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Langley Aeronautical Laboratory
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Langley Aeronautical Laboratory
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**Langley Aeronautical Laboratory**represents an institution, an association, or corporate body that is associated with resources found in**University of Oklahoma Libraries**.- Label
- Langley Aeronautical Laboratory

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- A Comparison of ignition characteristics of diesel fuels as determined in engines and in a constant-volumen bomb
- A Comparison of propeller and centrifugal fans for circulating the air in a wind tunnel
- A Comparison of several methods of measuring ignition lag in a compression-ignition engine
- A Comparison of several tapered wings designed to avoid tip stalling
- A Complete tank test of a flying-boat hull with a pointed step - N.A.C.A. Model No. 22
- A Complete tank test of a model of a flying-boat hull - N.A.C.A. Model No. 11
- A Complete tank test of a model of a flying-boat hull : N.A.C.A. Model No. 11-A
- A Complete tank test of a model of a flying-boat hull : N.A.C.A. Model No. 16
- A Dangerous seaplane landing condition
- A General tank test of a model of the hull of the British Singapore IIC flying boat
- A General tank test of a model of the hull of the P3M-1 flying boat including a special working chart for the determination of hull performance
- A Method of calculating the performance of controllable propellers, with sample computations
- A Method of estimating the aerodynamic effects of ordinary and split flaps of airfoils similar to the Clark Y
- A Method of estimating the critical buckling load for structural members
- A Method of rapidly estimating the position of the laminar separation point
- A Preliminary motion-picture study of combustion in a compression-ignition engine
- A Preliminary study of the prevention of ice on aircraft by the use of engine-exhaust heat
- A Study of autogiro rotor-blade oscillations in the plane of the rotor disk
- A Study of factors affecting the steady spin of an airplane
- A Summary of design formulas for beams having thin webs in diagonal tension
- A combined aerodynamic and guidance approach for a simple homing system
- A comparison of the aerodynamic characteristics of three normal and three reflexed airfoils in the variable density wind tunnel
- A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed
- A compilation of experimental flutter information
- A complete tank test on the hull of the Sikorsky S-40 flying boat - American Clipper Class
- A flight investigation of the transonic area rule for a 52.5° sweptback wind-body configuration at Mach numbers between 0.8 and 1.6
- A free-flight investigation at high subsonic and low supersonic speeds of the rolling effectiveness and drag of three spoiler controls having potentially low actuating-force requirements
- A free-flight investigation of the drag coefficients of two single-engine supersonic interceptor configurations from Mach number 0.8 to 1.90 to determine the effect of inlet and engine locations
- A free-flight investigation of the effects of simulated sonic turbojet exhaust on the drag of a boattail body with various jet sizes from Mach number 0.87 to 1.50
- A general tank test of NACA model 11-C flying-boat hull, including the effect of changing the plan form of the step
- A low-speed investigation of a thin 60° delta wing equipped with a double slotted flap to determine the chordwise pressure distribution and the effect of vane size
- A method for designing low-drag nose-inlet-body combinations for operation at moderate supersonic speeds
- A method for reducing the temperature of exhaust manifolds
- A method for the design of porous-wall wind tunnels
- A note on the drag due to lift of delta wings at Mach numbers up to 2.0
- A preliminary investigation of aerodynamic characteristics of small inclined air outlets at transonic Mach numbers
- A preliminary wind-tunnel investigation of flutter characteristics of delta wings
- A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M : 1.59 and angles of attack up to 36°
- A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel
- A proposed ram-jet control system operated by use of diffuser pressure recovery
- A simplified mathematical model for calculating aerodynamic loading and downwash for midwing wing-fuselage combinations with wings of arbitrary plan form
- A simplified method for approximating the transient motion in angles of attack and sideslip during a constant rolling maneuver
- A simplified method for the calculation of airfoil pressure distribution
- A study of means for rationalizing airplane design loads
- A study of the effect of aftercooling on the power and the weight of a 2000-horsepower air-cooled engine installation
- A study of the response of panels to random acoustic excitation
- A summary of drag results from recent Langley full-scale-tunnel tests of Army and Navy airplanes
- A tabulation of wind-tunnel pressure data at Mach numbers of 1.61 and 2.01 of five swept wings of the same plan form but different surface shapes
- A theoretical and experimental study of wind-tunnel-wall effects on oscillating air forces for two-dimensional subsonic compressible flow
- A transonic wind-tunnel investigation of the effects of nacelles on the aerodynamic characteristics of a complete model configuration
- A transonic wind-tunnel investigation of the longitudinal force and moment characteristics of two delta wings and one clipped-tip delta wing of 4 percent thickness on a slender body
- A warning concerning the take-off with heavy load
- A wind-tunnel investigation of the aerodynamic characteristics of a full-scale supersonic-type three-blade propeller at Mach numbers to 0.96
- A wind-tunnel investigation of the development of lift on wings in accelerated longitudinal motion
- A wind-tunnel investigation of the first-order vibratory stresses on a full-scale supersonic-type propeller operating in an asymmetric air flow
- Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps
- Adhesion of ice in its relation to the de-icing of airplanes
- Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and low supersonic speeds
- Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section
- Aerodynamic characteristics at high speeds of full-scale propellers having different shank designs
- Aerodynamic characteristics at small scale and a Mach number of 1.38 of untapered wings having M and W plan forms
- Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 1.60 of nacelle shape and position on the aerodynamic characteristics in pitch of two wing-body combinations with a 47° sweptback wings
- Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch at M = 2.0
- Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a diamond-plan-form wing aspect ration 3.08 and a low, swept horizontal tail
- Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)
- Aerodynamic characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8
- Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 to 180 degrees
- Aerodynamic characteristics of a canard-balanced, free-floating, all-movable stabilizer as obtained from rocket-powered-model flight tests and low-speed wind-tunnel tests
- Aerodynamic characteristics of a circular cylinder at Mach number 6.86 and angles of attack up to 90 degrees
- Aerodynamic characteristics of a delta wing with leading edge swept back 45 degrees, aspect ratio 4, and NACA 65A006 airfoil section : Transonic-bump method
- Aerodynamic characteristics of a number of modified NACA four-digit-series airfoil sections
- Aerodynamic characteristics of a refined deep-step planing-tail flying-boat hull with various forebody and afterbody shapes
- Aerodynamic characteristics of a small-scale shrouded propeller at angles of attack from 0 to 90 degrees
- Aerodynamic characteristics of a spoiler-slot-deflector control on a 45° sweptback wing at Mach numbers of 1.61 and 2.01
- Aerodynamic characteristics of a two-blade NACA 10-(3)(062)-045 propeller and of a two-blade NACA 10-(3)(08)-045 propeller
- Aerodynamic characteristics of a wing with quarter-chord line swept back 35°, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section : Transonic-bump method
- Aerodynamic characteristics of a wing with quarter-chord line swept back 45 degrees, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section : Transonic-bump method
- Aerodynamic characteristics of anemometer cups
- Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds
- Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 to 20 degrees at high subsonic speeds
- Aerodynamic characteristics of several airfoils of low aspect ratio
- Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)
- Aerodynamic characteristics of three deep-step planing-tail flying-boat hulls and a transverse-step hull with extended afterbody
- Aerodynamic characteristics of two delta wings and two trapezoidal wings at Mach number of 4.04
- Aerodynamic characteristics over a Mach number range of 1.40 to 2.78 of a rocket-propelled airplane configuration having a low 52.2° delta wing and an unswept horizontal tail
- Aerodynamic effects of a split flap on the spinning characteristics of a monoplane model
- Aerodynamic investigation at Mach number 1.92 of a rectangular wing and tail and body configuration and Its components
- Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees
- Aerodynamic investigation of a parabolic body of revolution at Mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base
- Aerodynamic load measurements and opening characteristics of automatic leading-edge slats on a 45° sweptback wing at transonic speeds
- Aerodynamic loading characteristics in sideslip of a 45° sweptback wing with and without a fence at high subsonic speeds
- Aerodynamic losses in low-pressure tailpipe exhaust ducts for rocket-propelled aircraft
- Aerodynamic rolling and yawing moments produced by floating wing-tip ailerons, as measured by the spinning balance
- Aerodynamic tests of a low aspect ratio tapered wing with an auxiliary airfoil for use on tailless airplanes
- Aerodynamic tests of a low aspect ratio tapered wing with various flaps, for use on tailless airplanes
- Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5
- Aerodynamics of a rectangular wing of infinite aspect ratio at high angles of attack and supersonic speeds
- Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow
- Air-flow and power characteristics of the Langley 16-foot transonic tunnel with slotted test section
- Air-flow surveys in the vicinity of representative NACA 1-series cowlings
- Airfoil in sinusoidal motion in a pulsating stream
- Airfoil lift with changing angle of attack
- Airfoil section characteristics at high angles of attack
- Alterations and tests of the "Farnboro" engine indicator
- Ambient pressure determination at high altitudes by use of free-molecule theory
- An Approximate spin design criterion for monoplanes
- An Experimental investigation of the normal acceleration of an airplane model in a gust
- An accurate and rapid method for the design of supersonic nozzles
- An aerodynamic and hydrodynamic investigation of two multi-jet water-based aircraft having low transonic drag rise
- An air-flow-direction pickup suitable for telemetering use on pilotless aircraft
- An airborne indicator for measuring vertical velocity of airplanes at wheel contact
- An analysis of acceleration, airspeed, and gust-velocity data from a four-engine transport airplane in operations on an eastern United States route
- An analysis of acceleration, airspeed, and gust-velocity data from one type of four-engine transport airplane operated over two domestic routes
- An analysis of accelerations, airspeeds, and gust velocities from three commercial operations of one type of medium-altitude transport airplane
- An analysis of buzzing in supersonic ram jets by a modified one-dimensional nonstationary wave theory
- An analysis of ducted-airfoil ram jets for supersonic aircraft
- An analysis of estimated and experimental transonic downwash characteristics as affected by plan form and thickness for wing and wing-fuselage configurations
- An analysis of the normal accelerations and airspeeds of several Lockheed Constellation L-649 airplanes in postwar commercial transport operations over the eastern part of the United States
- An analysis of the pressure distribution measured on a body of revolution at transonic speeds in the slotted test section of the Langley 8-foot transonic tunnel
- An application of the von Karman-Millikan laminar boundary-layer theory and comparison with experiment
- An approximate determination of the power required to move control surfaces as related to control-booster design
- An experimental and theoretical investigation at high subsonic speeds of the effects of horizontal-tail height on the aerodynamic characteristics in sideslip of an unswept, untapered tail assembly
- An experimental investigation of the effect of high-pressure tailpipe length on the performance of solid-propellant motors for rocket-powered aircraft
- An experimental investigation of the effects of Mach number, stabilizer dihedral, and fin torsional stiffness on the transonic flutter characteristics of a tee-tail
- An experimental investigation of the transonic-flow-generation and shock-wave-reflection characteristics of a two-dimensional wind tunnel with 17-percent-open perforated walls
- An experimental study of a method of designing the sweptback-wing - fuselage juncture for reducing the drag at transonic speeds
- An experimental study of five annular air inlet configurations at subsonic and transonic speeds
- An experimental transonic investigation of a 45° sweptback wing-body combination with several types of body indentation with theoretical comparisons included
- An initial experimental study of the effect of variations in frequency and impulse on the reduction in temperature recovery factor afforded by large-scale unsteady flow
- An investigation at Mach numbers 1.94 and 2.41 of jet effects upon the longitudinal and directional stability of a general aircraft configuration employing wing-tip-mounted nacelles
- An investigation in the Langley 20-foot free-spinning tunnel of the spin and recovery characteristics of a 1/30-scale model of the Bell X-2 airplane
- An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and a 40° sweepback : pressure distribution measurements of the interference effect of the wing on the fuselage at Mach numbers of 1.40 and 1.59
- An investigation of several NACA 1-series nose inlets with and without protruding central bodies at high-subsonic Mach numbers and at a Mach number of 1.2
- An investigation of the drag characteristics of speed brakes for Mach numbers from 0.20 to 1.30
- An investigation of the effects of a geometric twist on the aerodynamic loading characteristics of a 45° sweptback wing-body configuration at transonic speeds
- An investigation of the hydrodynamic characteristics of a dynamic model of a transonic seaplane design having a planing-tail hull
- Analog-computer investigation of effects of friction and preload on the dynamic longitudinal characteristics of a pilot-airplane combination
- Analysis and comparison with theory of flow-field measurements near a lifting rotor in the Langley full-scale tunnel
- Analysis and model tests of autogiro jump take-out
- Analysis and modification of theory for impact of seaplanes on water
- Analysis of a spin and recovery from time histories of attitudes and velocities as determined for a dynamic model of a contemporary fighter airplane in the free-spinning tunnel
- Analysis of accelerations, gust velocities, and airspeeds from operations of a twin-engine transport airplane on a transcontinental route from 1950 to 1952
- Analysis of aerodynamic blade-loading-limit parameters for NACA 65-(C[sub zeta]0A10) 10 compressor-blade sections at low speeds
- Analysis of an induction blowdown supersonic tunnel
- Analysis of available data on the effects of tabs on control-surface hinge moments
- Analysis of behavior of simply supported flat plates compressed beyond the buckling load into the plastic range
- Analysis of cylinder-pressure-indicator diagrams showing effects of mixture strength and spark timing
- Analytical and experimental studies of spherical solid-propellant rocket motors
- Application of nonlinear aerodynamic stability characteristics to simplify missile control and guidance systems
- Application of transonic area rule to a sharp-lipped ducted nacelle
- Approximate stress analysis of multistringer beams with shear deformation of the flanges
- Average skin-friction coefficients from boundary-layer measurements on an ogive-cylinder body in flight at supersonic speeds
- Basic requirements of fuel-injection nozzles for quiescent combustion chambers
- Boosted performance of a compression-ignition engine with a displacer piston
- Bypass-duct design for use with supersonic inlets
- Calculated effect of various types of flap on take-off over obstacles
- Calculated effects of the lateral acceleration derivatives on the dynamic lateral stability of a delta-wing airplane
- Carbon-monoxide indicators for aircraft
- Characteristics of an airfoil as affected by fabric sag
- Characteristics of two sharp-nosed airfoils having reduced spinning tendencies
- Charts for calculation of the critical compressive stress for local instability of idealized web- and T-stiffened panels
- Charts for calculation of the critical stress for local instability of columns with I-, Z-, channel, and rectangular-tube section
- Charts for determining the pitching moment of tapered wings with sweepback and twist
- Charts for estimation of the characteristics of a helicopter rotor in forward flight : 1 - Profile drag-lift ratio for untwisted rectangular blades
- Charts showing stability and control characteristics of airplanes in flight
- Circular motion of bodies of revolution
- Combustion-engine temperatures by the sodium line-reversal method
- Comparative performance of a Powerplus vane-type supercharger and an N.A.C.A. roots-type supercharger
- Comparative performance of engines using a carburetor, manifold injection, and cylinder injection
- Comparison of NACA 65-series compressor-blade pressure distributions and performance in a rotor and in cascade
- Comparison of lift-curve slopes for a model tested in two slotted tunnels of different sizes at high subsonic speeds
- Comparison of profile-drag and boundary-layer measurements obtained in flight and in the full-scale wind tunnel
- Comparison of semispan data obtained in the Langley two-dimensional low-turbulence pressure tunnel and full-span data obtained in the Langley 19-foot pressure tunnel for a wing with a 40° sweepback of the 0.27-chord line
- Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings
- Comparison of three methods for calculating the compressive strength of flat and slightly curved sheet and stiffner combinations
- Complete tank tests of two flying-boat hulls with pointed steps : N.A.C.A. Models 22-A and 35
- Compression-ignition engine performance with undoped and doped fuel oils and alcohol mixtures
- Compression-ignition engine tests of several fuels
- Considerations affecting hydro-ski airplane design
- Considerations of air flow in combustion chambers of high-speed compression-ignition engines
- Considerations of the take-off problem
- Control hinge-movement and effectiveness characteristics of several interchangeable tip controls on a 60° delta wing at Mach numbers of 1.41, 1.62, and 1.96
- Critical combinations of longitudinal and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation
- Critical stress for an infinitely long flat plate with elastically restrained edges under combined shear and direct stress
- Damping in roll of models with 45°, 60°, and 70° delta wings determined at high subsonic, transonic, and supersonic speeds with rocket -powered models
- Damping-in-pitch characteristics at high subsonic and transonic speeds of four 35° sweptback wings
- Description and analysis of a rocket-vehicle experiment on flutter involving wing deformation and body motions
- Design and evaluation of a turbojet-exhaust simulator with a solid-propellant rocket motor for free-flight research
- Design and tests of a six-stage axial-flow compressor having a tip speed of 550 feet per second and a flat operating characteristic at constant speed
- Determination by the free-fall method of the longitudinal stability and control characteristics of a 1/4-scale model of the Bell XS-1 airplane at transonic speeds
- Determination of propeller deflection by means of static load tests on models
- Determination of the stability and control characteristics of airplanes from tests of powered models
- Development of the NACA slot-lip aileron
- Discharge characteristics of a simulated unit injection system
- Discussion of three-dimensional oscillating air forces based on wind-tunnel measurements
- Downwash, sidewash, and wave survey behind a 42° sweptback wing at a Reynolds number of 6.8 x 106 with and without a simulated ground
- Drag and cooling with various forms of cowling for a "Whirlwind" engine in a cabin fuselage
- Drag due to lift at Mach numbers up to 2.0
- Drag measurements at transonic speeds of two bodies of fineness ratio 9 with different locations of maximum body diameter
- Drag of exposed fittings and surface irregularities on airplane fuselages
- Drag of prestone and oil radiators on the YO-31A airplane
- Drag tests of 4/9-scale model engine nacelles with various cowlings
- Effect at high subsonic speeds of fuselage forebody strakes on the static stability and vertical-tail-load characteristics of a complete model having a delta wing
- Effect of a wing leading-edge flap and chord-extension on the high subsonic control characteristics of an aileron located at two spanwise positions
- Effect of airfoil profile of symmetrical sections on the low-speed rolling derivatives of 45° sweptback-wing models of aspect ratio 2.61
- Effect of changes in tail arrangement upon the spinning of a low-wing monoplane model
- Effect of combustion-chamber shape on the performance of a prechamber compression-ignition engine
- Effect of compressibility on the hovering performance of two 10-foot-diameter helicopter rotors tested in the Langley full-scale tunnel
- Effect of convergent ejector nozzles on the boattail drag of a 16° conical afterbody at Mach number of 0.6 to 1.26
- Effect of downwash on the estimated elevator deflection required for trim of the XS-1 airplane at supersonic speeds
- Effect of engine operating conditions on the vaporization of safety fuels
- Effect of length of Handley Page tip slots on the lateral-stability factor, damping in roll
- Effect of normal pressure on the critical compressive and shear stress of curved sheet
- Effect of normal pressure on the critical compressive stress of curved sheet
- Effect of nose shape on the characteristics of symmetrical airfoils
- Effect of propeller-axis angle of attack on thrust distribution over the propeller disk in relation to wake-survey measurement of thrust
- Effect of retractable-spoiler location on rolling- and yawing-moment coefficents
- Effect of some section modifications and protuberances on the zero-lift drag of delta wings at transonic and supersonic speeds
- Effect of stabilizer location upon pitching and yawing moments in spins as show n by tests with the spinning balance
- Effect of surface roughness on characteristics of spherical shock waves
- Effect of the reservoir volume on the discharge pressures in the injection system of the N.A.C.A. spray photography equipment
- Effect of the surface conditions of a wing on the aerodynamic characteristics of an airplane
- Effect of thickness, camber, and thickness distribution on airfoil characteristics at Mach numbers up to 1.0
- Effect of yaw and angle of attack on pressure recovery and mass-flow characteristics of a rectangular supersonic scoop inlet at a Mach number of 2.71
- Effects of a sweptback hydrofoil on the force and longitudinal stability characteristics of a typical high-speed airplane
- Effects of aspect ratio on air flow at a high subsonic mach numbers
- Effects of compressibility on maximum lift coefficients for six propeller airfoils
- Effects of fences, leading-edge chord-extensions, bound-layer ramps, and trailing-edge flaps on the longitudinal stability of a twisted and cambered 60° sweptback-wing--indented-body configuration at transonic speeds
- Effects of overhang balance on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60 degree delta wing at transonic and supersonic speeds
- Effects of size of external stores on the aerodynamic characteristics of an unswept and a 45° sweptback wing of aspect ratio 4 and a 60° delta wing at Mach numbers of 1.41, 1.62, and 1.96
- Effects of some external-store mounting arrangements and store shapes on the buffet and drag characteristics of wingless rocket-powered models at Mach numbers from 0.7 to 1.4
- Effects of twist and camber on the low-speed longitudinal stability characteristics of a 45° swept-back wing of aspect ratio 8 at Reynolds numbers from 1.5 x 106 to 4.8 x 10 as determined by pressure distributions, force tests, and calculations
- Effects of wing position and vertical-tail configuration on stability and control characteristics of a jet-powered delta-wing vertically rising airplane model
- Effects of wing-body geometry on the lateral-flow angularities at subsonic speeds
- Effects on adjacent surfaces from the firing of rocket jets
- Engine performance with a hydrogenated safety fuel
- Error in airspeed measurement due to static-pressure field ahead of an open-nose air-inlet model at transonic speeds
- Estimation of lift and drag of airfoils at near sonic speeds and in the presence of detached shock waves
- Estimation of moments of inertia of airplanes from design data
- Experimental aerodynamic forces and moments at low speed of a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage combination
- Experimental and analytical investigation of flutter of a nonuniform sweptback cantilever wing with two concentrated weights
- Experimental and theoretical determination of thermal stresses in a flat plate
- Experimental and theoretical studies of panel flutter at Mach number 1.2 to 3.0
- Experimental convective heat transfer to a 4-inch and 6-inch hemisphere at Mach numbers from 1.62 to 3.04
- Experimental convective heat transfer to a 4-inch and 6-inch hemisphere at Mach numbers from 1.62 to 3.04
- Experimental determination of damping in pitch of swept and delta wings at supersonic Mach numbers
- Experimental determination of effect of structural rigidity on rolling effectiveness of some straight and swept wings at Mach numbers from 0.7 to 1.7
- Experimental determination of the effects of frequency and amplitude of oscillation on the roll-stability derivatives for a 60° delta-wing airplane model
- Experimental investigation of an axial-flow supersonic compressor having sharp leading-edge blades with an 8-percent mean thickness-chord ratio
- Experimental investigation of flow through three highly loaded inlet guide vanes having different spanwise circulation gradients
- Experimental investigation of the forces and moments due to sideslip of a series of triangular vertical- and horizontal-tail combinations at Mach numbers of 1.62, 1.93, and 2.41
- Experimental investigation of the mixing loss behind trailing edge of a cascade of three 90° supersonic turning passages
- Experiments on the distribution of fuel in fuel sprays
- Exploratory investigation of the moments on oscillating control surfaces at transonic speeds
- Exploratory rocket flight tests to investigate the use of a freely spinning monoplane tail for stabilizing a body
- Factors affecting the maximum lift-drag ratio at high supersonic speeds
- Factors affecting transition at supersonic speeds
- Flight determination of drag and pressure recovery of two scoop inlets located at maximum-body-diameter station at Mach numbers from 0.8 to 1.8
- Flight determination of the drag and pressure recovery of an NACA 1-40-250 nose inlet at Mach numbers from 0.9 to 1.8
- Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift
- Flight investigation at high-subsonic, transonic, and supersonic speeds to determine zero-lift drag of fin-stabilized bodies of revolution having fineness ratios of 12.5, 8.91, and 6.04 and varying positions of maximum diameter
- Flight investigation of a ram jet burning magnesium slurry fuel and having a conical shock inlet designed for a Mach number of 4.1
- Flight investigation of a supersonic canard missile equipped with an auxiliary damping-in-pitch control system
- Flight investigation of an aileron and a spoiler on a wing of the X-3 airplane plan form at Mach numbers from 0.5 to 1.6
- Flight investigation of the zero-lift drag of two ram-jet missile configurations at Mach numbers from 1.0 to 1.89
- Flight measurement of the stability characteristics of the Douglas D-558-1 airplane (Buaero no. 37971) in sideslips
- Flight tests at transonic and supersonic speeds of an airplane-like configuration with a thin straight sharp-edge wings and tail surfaces
- Flight tests of N.A.C.A. nose-slot cowlings on the BFC-1 airplane
- Flight tests of a balanced split flap with particular reference to rapid operation
- Flight tests of a model having self-supporting fuel-carrying panels hinged to the wing tips
- Flight tests of tractable ailerons on a highly tapered wing
- Flight tests to determine the effect of a fixed auxiliary airfoil on the lift and drag of a parasol monoplane
- Flow observations with tufts and lampblack of the stalling of four typical airfoil sections in the N.A.C.A. variable-density tunnel
- Flutter at very high speeds
- Flutter characteristics of swept wings at transonic speeds
- Flutter investigation at low speed of a 40 degree sweptback wing with pylon-mounted stores, tested as a semispan-cantilever wing and as a full-span wing on a towed airplane model
- Flutter investigation of a true-speed dynamic model with various tip-tank configurations
- Flutter investigation of two thin, low-aspect-ratio, swept, solid, metal wings in the transonic range by use of free-falling body
- Flutter of a 60° delta wing (NACA 65A003 airfoil) encountered at supersonic speeds during the flight test of a rocket-propelled model
- Free-flight measurements of aerodynamic heat transfer to Mach number 3.9 and of drag to Mach number 6.9 of a fin-stabilized cone-cylinder configuration
- Free-flight measurements of aerodynamic heat transfer to Mach number 3.9 and of drag to Mach number 6.9 of a fin-stabilized cone-cylinder configuration
- Free-flight measurements of the rolling effectiveness and drag of trailing-edge spoilers on a tapered sweptback wing at Mach numbers between 0.6 and 1.4
- Free-jet tests of a 1.1-inch-diameter supersonic ram-jet engine
- Friction of compression-ignition engines
- Full scale drag tests on various parts of Sperry Messenger airplane
- Full-scale drag tests of landing lamps
- Full-scale force and pressure-distribution tests on a tapered U.S.A. 45 Airfoil
- Full-scale wind-tunnel and flight tests of a Fairchild 22 airplane equipped with a Fowler flap
- Full-scale wind-tunnel research on tail buffeting and wing-fuselage interference of a long-wing monoplane
- Full-scale wind-tunnel tests to determine a satisfactory location for a service pitot-static tube on a low-wing monoplane
- Further measurements of normal accelerations on racing airplanes
- Hazards to aircraft due to electrical phenomena
- Heat dissipation from a finned cylinder at different fin-plane / air-stream angles
- Heat transfer and pressure measurement on a 5-inch hemispherical concave nose at a Mach number of 2.0
- Heat transfer and pressure measurement on a 5-inch hemispherical concave nose at a Mach number of 2.0
- Heat transfer and skin friction for turbulent boundary layers on heated or cooled surfaces at high speeds
- Heat transfer and skin friction for turbulent boundary layers on heated or cooled surfaces at high speeds
- Heat transfer to bodies at angles of attack
- Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29°
- Hydrodynamic and aerodynamic tests of a family of models of seaplane floats with varying angles of dead rise. : N.A.C.A. models 57-A, 57-B, and 57-C
- Hydrodynamic and aerodynamic tests of four models of outboard floats (N.A.C.A. Models 51-A, 51-B, 51-C, and 51-D)
- Hydrodynamic-stability tests of a model of a flying boat and of a planing surface having a small downward projection (hook) on the planing bottom near the step
- Ice prevention on aircraft by means of engine exhaust heat and a technical study of heat transmission from a Clark Y airfoil
- Influence of fuel-oil temperature on the combustion in a prechamber compression-ignition engine
- Influence of several factors on ignition lag in a compression-ignitiion engine
- Influence of wall boundary layer upon the performance of an axial-flow fan rotor
- Initial experimental investigation of the aerodynamic load on the wing of a model caused by a blast-induced gust that increases the angle of attack into the stall region
- Interaction of moving shocks and hot layers
- Intermittent-flow coefficients of a poppet valve
- Investigation at Mach numbers from 0.80 to 1.43 of pressure and load distributions over a thin 45° sweptback highly tapered wing in combination with basic and indented bodies
- Investigation at supersonic speeds of the variation with Reynolds number and Mach number of the total, base, and skin-friction drag of seven boattail bodies of revolution designed for minimum wave drag
- Investigation at transonic speeds of a fixed divergent ejector installed in a single-engine fighter model
- Investigation at transonic speeds of aerodynamic characteristics of an unswept semielliptical air inlet in the root of a 45° sweptback wing
- Investigation at transonic speeds of the hinge-moment characteristics of a 1/8-scale model of the X-1E aileron
- Investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections
- Investigation of a simple device for preventing separation due to shock and boundary-layer interaction
- Investigation of an impulse axial-flow compressor
- Investigation of an impulse axial-flow compressor rotor over a range of blade angles
- Investigation of fixed-geometry supersonic inlets with bypass ducts for matching turbojet-engine air-flow requirements over a range of transonic and supersonic speeds
- Investigation of intake ducts for a high-speed subsonic jet-propelled airplane
- Investigation of the NACA 4-(0)(03)-45 two-blade propeller at forward Mach numbers to 0.925
- Investigation of the NACA 4-(4)(06)-04 two-blade propeller at forward Mach numbers to 0.925
- Investigation of the NACA-4-(3)(08)-03 two-blade propeller at forward Mach numbers to 0.925
- Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0.18 chord
- Investigation of the aerodynamic characteristics in pitch and sideslip of a 45° swept-wing airplane configuration with various vertical locations of the wing and horizontal tail : Static lateral and directional stability ; Mach numbers of 1.41 and 2.01
- Investigation of the aerodynamic characteristics of the NACA RM-10 missile (with fins) at a Mach number of 1.62 in the Langley 9-inch supersonic tunnel
- Investigation of the drag of blunt-nosed bodies of revolution in free flight at Mach numbers from 0.6 to 2.3
- Investigation of the dynamic lateral stability and control characteristics of a model of a fighter airplane without a horizontal tail and equipped with either single or twin vertical tails
- Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45° sweptback wing of aspect ratio 4
- Investigation of the effects of model scale and stream Reynolds number on the aerodynamic characteristics of two rectangular wings at supersonic speeds on the Langley 9-inch supersonic tunnel
- Investigation of the fatigue strength of a full-scale airplane wing structures
- Investigation of the static lateral stability and aileron characteristics of a 0.067-scale model of the Bell X-2 airplane at Mach number of 2.29, 2.78, 3.22, and 3.71
- Investigation of the variation with Reynolds number of the base, wave, and skin-friction drag of a parabolic body of revolution (NACA RM-10) at Mach numbers of 1.62, 1.93, and 2.41 in the Langley 9-inch supersonic tunnel
- Investigation of three tapered 45° sweptback cambered and twisted wings covering a simultaneous variation in aspect ratio and thickness ratio and of one related symmetrical wing at transonic speeds by the wing-flow method
- Investigation of transonic flutter characteristics of a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6
- Investigation of wing flutter at transonic speeds for six systematically varied wing plan forms
- Investigation toward simplification of missile control systems
- Investigations at supersonic speeds of 22 triangular wings representing two airfoil sections for each of 11 apex angles
- Investigations at supersonic speeds of the base pressure on bodies of revolution with and without sweptback stabilizing fins
- Jet effects on longitudinal trim of an airplane configuration measured at Mach numbers between 1.2 and 1.8
- Landing characteristics of an autogiro
- Landing conditions for large airplanes in routine operations
- Landing-shock recorder
- Langley 9-inch supersonic tunnel tests of several modifications of a supersonic missile having tandem cruciform lifting surfaces : three-component data results of models having ratios of wing span to tail span less than 1
- Langley full-scale tunnel investigation of the factors affecting the directional stability and trim characteristics of a fighter-type airplane
- Large-scale flight measurements of zero-lift drag and low-lift drag of 10 wing-body configurations at Mach numbers from 0.8 to 1.6
- Lateral-control investigation of flap-type controls on a wing with quarter-chord line sweptback 35°, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : Transonic-bump method
- Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation
- Lift, drag, and static longitudinal stability data from an exploratory investigation at a Mach number of 6.86 of an airplane configuration having a wing of trapezoidal plan form
- Lift-curve slopes determined in flight on a flexible swept-wing jet bomber
- Limitations of the pilot in applying forces to airplane controls
- Load distributions associated with controls at supersonic speeds
- Loads associated with spoilers at supersonic speeds
- Loads imposed on intermediate frames of stiffened shells
- Loads on external stores at transonic and supersonic speeds
- Loads on thin wings at transonic speeds
- Loads on wings due to spoilers at subsonic and transonic speeds
- Local heat transfer to blunt noses at high supersonic speeds
- Local instability of centrally loaded columns of channel section and Z-section
- Local instability of symmetrical rectangular tubes under axial compression
- Longitudinal aerodynamic characteristics of a model airplane configuration equipped with a scaled X-1 airplane wing
- Longitudinal stability and control characteristics from a flight investigation of a cruciform canard missile configuration having an exposed wing-canard area ratio of 16:1
- Longitudinal stability and trim of two rocket-propelled airplane models having 45° sweptback wings and tails with the horizontal tail mounted in two positions
- Longitudinal stability characteristics at transonic speeds of a rocket-propelled model of an airplane having a 45 degree swept wing of aspect ratio 6.0
- Low-speed cascade investigation of loaded leading-edge compressor blades
- Low-speed characteristics in pitch of a 34° sweptforward wing with circular-arc airfoil sections
- Low-speed pitching derivatives of low-aspect-ratio wings of triangular and modified triangular plan forms
- Low-speed static lateral stability characteristics of a canard model having a 60° triangular wing and horizontal tail
- Low-speed static stability characteristics of a cambered-delta-wing model
- Low-speed wind-tunnel investigation of a triangular sweptback air inlet in the root of a 45 degree sweptback wing
- Low-speed wind-tunnel investigation of jet control on a 35° swept wing
- Mass distribution and performance of free flight models
- Measurement of the moments of inertia of full scale airplanes
- Measurements of aerodynamic heat transfer in turbulent separated regions at a Mach number of 1.8
- Measurements of aerodynamic heating obtained during demonstration flight tests of the Douglas D-558-II airplane
- Measurements of fluctuating pressures on the wing of a sweptback wind-body combination in the Langley 16-foot transonic tunnel
- Mechanical properties of pneumatic tires with special reference to modern aircraft tires
- Metal-truss wing spars
- Methods of visually determining the air flow around airplanes
- Miscellaneous directional-stability data for several airplane-like configurations from rocket-model tests at transonic speeds
- Moment of inertia and damping of fluid in tanks undergoing pitching oscillations
- NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results
- Noise from propellers with symmetrical sections at zero blade angle, II
- Normal force, center of pressure, and zero-lift drag of several ballistic-type missiles at Mach numbers of 4.05
- Notes on the technique of landing airplanes equipped with wing flaps
- On slender-body theory at transonic speeds
- On slender-body theory at transonic speeds
- Penetration and duration of fuel sprays from a pump injection system
- Performance characteristics of two 6° and two 12° diffusers at high flow rates
- Performance of air-cooled engine cylinders using blower cooling
- Performance of compressor blade cascades at high Mach numbers
- Performance tests of a single-cylinder compression-ignition engine with a displacer piston
- Piloting technique for recovery from spins
- Power-on longitudinal-stability and control tests of the 1/8-scale model of the Brewster F2A airplane equipped with full-span slotted flaps and a new horizontal tail
- Power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps
- Precision of wing sections and consequent aerodynamic effects
- Preliminary biplane tests in the variable density wind tunnel
- Preliminary evaluation of turbine performance with variable-area turbine nozzles in a turbojet engine
- Preliminary investigation at low speeds of swept wings in rolling flow
- Preliminary investigation of a variable Mach number two-dimensional supersonic tunnel of fixed geometry
- Preliminary investigation of lithium hydride as a high-temperature internal coolant
- Preliminary investigation of rolling moments obtained with spoilers on both slotted and plain wings
- Preliminary investigation of self-excited vibrations of single planing surfaces
- Preliminary investigation of shock-wave reflections in a small closed ballistic range with various types of walls
- Preliminary investigation of the compressive strength and creep lifetime of 2024-T3 (formerly 24S-T3) aluminum-alloy plates at elevated temperatures
- Preliminary investigation of the compressive strength and creep lifetime of 2024-T3 (formerly 24S-T3) aluminum-alloy plates at elevated temperatures
- Preliminary investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61
- Preliminary investigation of the failure of pressurized stiffened cylinders
- Preliminary investigation on boundary layer control by means of suction and pressure with the U.S.A. 27 airfoil
- Preliminary investigations of strength characteristics of structural elements at elevated temperatures
- Preliminary photomicrographic studies of fuel sprays
- Preliminary report on the flat-top lift curve as a factor in control at low speed
- Preliminary results for a free-flight investigation at transonic and supersonic speeds of longitudinal stability and control characteristics of an airplane configuration with a thin straight wing of aspect ratio 3
- Preliminary results from a free-flight investigation of boundary-layer transition and heat transfer on a highly polished 8-inch-diameter hemisphere-cylinder at Mach numbers up to 3 and Reynolds numbers based on a length of 1 foot up to 17.7 x 106
- Preliminary results of stability calculations for the bending of box beams with longitudinally stiffened covers connected by posts
- Preliminary results of supersonic-jet tests of simplified wing structures
- Preliminary results of the flight investigation between Mach numbers of 0.80 and 1.36 of a rocket-powered model of a supersonic airplane configuration having a tapered wing with circular-arc sections and 40° sweepback
- Preliminary studies of manned satellites wingless configuration : nonlifting
- Preliminary study of some factors which affect the stall-flutter characteristics of thin wings
- Preliminary tests on the vaporization of fuel sprays
- Pressure distribution on wing ribs of the VE-7 and TS airplanes in flight
- Pressure loads produced on a flat-plate wing by rocket jets exhausting in a spanwise direction below the wing and perpendicular to a free-stream flow of Mach number 2.0
- Pressure measurements on a body of revolution in the Langley 16-foot transonic tunnel and a comparison with free-fall data
- Principles of moment distribution applied to stability of structures composed of bars or plates
- Procedure for determining speed and climbing performance of airships
- Propeller vibrations and the effect of the centrifugal force
- Recent information on flap and tip controls
- Remarks on the elastic axis of shell wings
- Resistance of a fifteen-centimeter disk
- Resistance of streamline wires
- Results of two experiments on flutter of high-aspect-ratio swept wings in the transonic speed range
- Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range
- Resume of air-load data on slats and flaps
- Rocket-model investigation of longitudinal stability and drag characteristics of an airplane configuration have a 60° delta wing and a high unwept horizontal tail
- Rocket-powered flight test of a roll-stabilized supersonic missile configuration
- Several factors affecting roll control systems of interceptors
- Shear lag in box beams methods of analysis and experimental investigations
- Shear-lag tests of a box beam with a highly cambered cover in tension
- Simplified aerodynamic analysis of the cyclogiro rotating wing system
- Simulation study of a high-performance aircraft including the effect on pilot control of large accelerations during exit and reentry flight
- Some characteristics of sprays obtained from pintle-type injection nozzles
- Some considerations concerning inlets and ducted bodies at Mach numbers from 0.8 to 2.0
- Some effects of external wing tip stores on the rolling effectiveness and drag of plain and half-delta tip ailerons on a 4-percent-thick tapered, unswept wing
- Some effects of fin plan form on the static stability of fin-body combinations at Mach number 4.06
- Some effects of tail height and wing plan form on the static longitudinal stability characteristics of a small-scale model at high subsonic speeds
- Some elementary principles of shell stress analysis with notes on the use of the shear center
- Some experimental studies of panel flutter at Mach number 1.3
- Some factors affecting the variation of pitching moment with sideslip of aircraft configurations
- Some flutter experiments at a Mach number of 1.3 on cantilever wings with a tubular and closed bodes at the tips
- Some internal-flow characteristics at zero flight speed of an annular supersonic inlet and an open-nose inlet with sharp and rounded lips
- Some low-speed wind-tunnel experiments pertaining to the longitudinal stability characteristics of a 35° swept-wing model and an unswept-wing model
- Some measurements at subsonic speeds of the aerodynamic forces and moments on two delta wings of aspect ratios 2 and 4 oscillating about the midchord
- Some measurements of aerodynamic forces and moments at subsonic speeds on a rectangular wing of aspect ratio 2 oscillating about the midchord
- Some notes on the aerodynamic loads associated with external-store installations
- Some notes on the numerical solution of shear-lag and mathematically related problems
- Some observations on loss of static strength due to fatigue cracks
- Sound measurements for five shrouded propellers at static conditions
- Span loadings due to wing twist at transonic and supersonic speeds
- Spinning and related problems at high angles of attack for high-speed airplanes
- Spinning characteristics of wings, II, Rectangular Clark Y biplane cellule -- 25 percent stagger ; 0 degree decalage ; gap/chord 1.0
- Stability of two rocket-propelled models having aspect-ratio-5 unswept tails on a long body for the Mach number range of 1.7 to 2.4
- Static-thrust tests of six rotor-blade designs on a helicopter in the Langley full-scale tunnel
- Strain measurements and strength tests of 25-inch diagonal-tension beams with single uprights
- Strength tests of thin-walled duralumin cylinders in combined transverse shear and bending
- Strength tests of thin-walled duralumin cylinders in pure bending
- Strength tests of thin-walled duralumin cylinders of elliptic section
- Strength tests on thin-walled duralumin cylinder in torsion
- Stresses around rectangular cut-outs in skin-stringer panels under axial loads - II
- Studies of the use of Freon-12 as a testing medium in the Langley low-turbulence pressure tunnel
- Study of open jet wind tunnel cones
- Subsonic flight investigation of methods to improve the damping of lateral oscillations by means of a viscous damper in the rudder system in conjunction with adjusted hinge-moment parameters
- Subsonic investigation of effects of body indentation on zero-lift drag characteristics of a 45° sweptback wing-body combination with natural and fixed boundary-layer transition through a range of Reynolds number from 1 x 106 to 8 x 106
- Summary of flutter experiences as a guide to the preliminary design of lifting surfaces on missiles
- Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957
- Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957
- Summary of recent theoretical and experimental work on box-beam vibrations
- Supersonic flutter of a 60° delta wing encountered during the flight test of a rocket-propelled model
- Surface pressure distributions on a large-scale 49° sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge
- Tables and charts for the evaluation of profile drag from wake surveys at high subsonic speeds
- Tables of stiffness and carry-over factor for flat rectangular plates under compression
- Tank tests of a family of flying-boat hulls
- Tank tests of a model of a flying boat hull with a fluted bottom
- Tank tests of a model of a flying-boat hull having a longitudinally concave planing bottom
- Tank tests of a model of the NC flying-boat hull - N.A.C.A. Model 44
- Tank tests of a model of the hull of the Navy PB-1 flying boat : N.A.C.A. Model 52
- Tank tests of auxiliary vanes as a substitute for planing area
- Tank tests of flat and v-bottom planing surfaces
- Tank tests of model 11-G flying-boat hull
- Tank tests of models of floats for single-float seaplanes : First series
- Tank tests of models of flying boat hulls having longitudinal steps
- Tank tests of three models of flying-boat hulls of the pointed-step type with different angles of dead rise - NACA model 35 series
- Tank tests of two floats for high-speed seaplanes
- Telemeter transmission at 219.5 megacycles from two rocket-powered models at Mach number up to 15.7
- Tensile properties of some sheet materials under rapid-heating conditions
- Tensile properties of some sheet materials under rapid-heating conditions
- Test data on the shear strength of joints assembled with round-head and brazier-head rivets
- Test of NACA 66,2-116, a : 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane
- Tests of 10 inch 24S-T aluminum-alloy shear panels with 1-1/2 inch holes : 2 - Panels having holes with notched edges
- Tests of N.A.C.A. airfoils in the variable-density wind tunnel : Series 20
- Tests of N.A.C.A. airfoils in the variable-density wind tunnel. : Series 24
- Tests of N.A.C.A. airfoils in the variable-density wind tunnel. : Series 43 and 63
- Tests of N.A.C.A. airfoils in the variable-density wind tunnel. : Series 44 and 64
- Tests of N.A.C.A. airfoils in the variable-density wind tunnel. : Series 45 and 65
- Tests of an N.A.C.A. 23012 airfoil with a slotted deflector flap
- Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons
- Tests of six symmetrical airfoils in the variable density wind tunnel
- Tests of the N.P.L. airship models in the variable density wind tunnel
- Tests of three tapered airfoils based on the N.A.C.A. 2200, the N.A.C.A.-M6, and the Clark Y sections
- Tests on thrust augmentors for jet propulsion
- The Aerodynamic Design of Supersonic Propellers From Structural Considerations
- The Aerodynamic analysis of the gyroplane rotating-wing system