#
Langley Aeronautical Laboratory
Resource Information
The organization ** Langley Aeronautical Laboratory** represents an institution, an association, or corporate body that is associated with resources found in **University of Oklahoma Libraries**.

The Resource
Langley Aeronautical Laboratory
Resource Information

The organization

**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

## Context

Context of Langley Aeronautical Laboratory#### Contributor of

- A combined aerodynamic and guidance approach for a simple homing system
- 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 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 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 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 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 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 flow investigation for location of angle of attack head on a JN4h airplane
- 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 Altitude chamber for the study and calibration of aeronautical instruments
- 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 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
- Bypass-duct design for use with supersonic inlets
- Calculated effects of the lateral acceleration derivatives on the dynamic lateral stability of a delta-wing airplane
- 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 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
- 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 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
- Considerations affecting hydro-ski airplane design
- 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 the stability and control characteristics of airplanes from tests of powered models
- 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 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
- 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 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 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 propeller-axis angle of attack on thrust distribution over the propeller disk in relation to wake-survey measurement of thrust
- Effect of some section modifications and protuberances on the zero-lift drag of delta wings at transonic and supersonic speeds
- Effect of surface roughness on characteristics of spherical shock waves
- 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
- 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
- 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
- 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 a model having self-supporting fuel-carrying panels hinged to the wing tips
- 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
- 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-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 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
- 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 conditions for large airplanes in routine operations
- 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
- Load distributions associated with controls at supersonic speeds
- Loads associated with spoilers at supersonic speeds
- 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
- 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
- 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
- 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
- Normal force, center of pressure, and zero-lift drag of several ballistic-type missiles at Mach numbers of 4.05
- On slender-body theory at transonic speeds
- On slender-body theory at transonic speeds
- Performance characteristics of two 6° and two 12° diffusers at high flow rates
- Performance of compressor blade cascades at high Mach numbers
- 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
- 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 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 investigations of strength characteristics of structural elements at elevated temperatures
- 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
- 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
- Recent information on flap and tip controls
- 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
- 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
- Simulation study of a high-performance aircraft including the effect on pilot control of large accelerations during exit and reentry flight
- 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 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 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
- 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
- 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
- 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
- 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 four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons
- The Aerodynamic Design of Supersonic Propellers From Structural Considerations
- The Aerodynamic analysis of the gyroplane rotating-wing system
- The Aerodynamic characteristics of a model wing having a split flap deflected downward and moved to the rear
- The Aerodynamic characteristics of airfoils as affected by surface roughness
- The Aerodynamic effect of a retractable landing gear
- The Aerodynamics of a wind-tunnel fan
- The Aileron as an aid to recovery from the spin
- The accuracy of the substitute-stringer approach for determining the bending frequencies of multistringer box beams
- The aerodynamic characteristics of an aspect-ratio-20 wing having thick airfoil sections and employing boundary-layer control by suction
- The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with sliding block for the Mach number range 1.27 to 2.75
- The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with sliding block for the Mach number range 1.27 to 2.75
- The aerodynamic design of high Mach number nozzles utilizing axisymmetric flow with application to a nozzle of square test section
- The aerodynamic drag of five models of side floats N.A.C.A. models 51-E, 51-F, 51-G, 51-H, and 51-J
- The aerodynamic drag of flying-boat hull models as measured in the NACA 20-foot wind tunnel - I
- The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel
- The aerodynamic forces and moments on a spinning model of the F4B-2 airplane as measured by the spinnning balance
- The behavior of beryllium and beryllium copper in a 4,000°F supersonic air jet at a Mach number of 2
- The development of an 8-inch by 8-inch slotted tunnel for Mach numbers up to 1.28
- The effect of a change in airfoil section on the hinge-moment characteristics of a half-delta tip control with a 60° sweep angle at a Mach number of 6.9
- The effect of high solidity on propeller characteristics at high forward speeds from wind-tunnel tests of the NACA 4-(3)(06.3)-06 and NACA 4-(3)(06.4)-09 two-blade propellers
- The effect of internal pressure on the buckling stress of thin-walled circular cylinders under torsion
- The effect of lateral area on the lateral stability and control characteristics of an airplane as determined by tests of a model in the Langley free-flight tunnel
- The effect of nose radius and shape of the aerodynamic characteristics of a fuselage and a wing-fuselage combination at angles of attack
- The effect of the inlet mach number and inlet-boundary-layer thickness on the performance of a 23° conical-diffuser-tail-pipe combination
- The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow
- The effects of fuselage size on the low-speed longitudinal aerodynamic characteristics of a thin 60° delta wing with and without a double slotted flap
- The effects of wing incidence on the aerodynamic loading characteristics of a sweptback wing-body combination at transonic speeds
- The flow past a straight- and a swept-wing-body combination and their equivalent bodies of revolution at Mach numbers near 1.0
- The flow past a straight- and a swept-wing-body combination and their equivalent bodies of revolution at Mach numbers near 1.0
- The performance of conical supersonic scoop inlets on circular fuselages
- The rolling moment due to sideslip of swept wings at subsonic and transonic speeds
- The static and dynamic longitudinal stability characteristics of some supersonic aircraft configurations
- The strength and stiffness of shear webs with and without lightening holes
- The strength and stiffness of shear webs with round lightening holes having 45 degree flanges
- The twisting effect at transonic speeds of spoiler ailerons on a 45° sweptback, aspect-ratio-4, tapered wing
- Theoretical analysis of the longitudinal behavior of an automatically controlled supersonic interceptor during the attack phase against maneuvering and nonmaneuvering targets
- Theoretical analysis of the rolling motions of aircraft using a flicker-type automatic roll stabilization system having a displacement-plus-rate response
- Theoretical investigation of some discontinuous yaw dampers
- Theoretical prediction of the side force on stores attached to configurations traveling at supersonic speeds
- Three-degree-of-freedom evaluation of the longitudinal transfer functions of a supersonic canard missile configuration including changes in forward speed
- Transient temperature distribution in an aerodynamically heated multiweb wing
- Transonic flight tests to compare the zero-lift drag on underslung and symmetrical nacelles varied chordwise at 40 percent semispan of a 45° sweptback, tapered wing
- Transonic flight tests to determine the effect of thickness ratio and plan-form modification on the zero-lift drag of a 45° sweptback wing
- Transonic flutter investigation of two 50° semispan modified-delta wings with tip ailerons
- Transonic investigation at lifting conditions of streamline contouring in the sweptback-wing-fuselage juncture in combination with the transonic area rule
- Transonic investigation of aerodynamic characteristics of a swept-wing fighter-airplane model with leading-edge droop in combination with outboard chord-extensions and notches
- Transonic longitudinal aerodynamic characteristics of a fighter-type airplane model with a low-aspect-ratio unswept wing and tee-tail
- Transonic longitudinal aerodynamic effects of sweeping up the rear of the fuselage of a rocket-propelled airplane model having no horizontal tail
- Transonic wind-tunnel investigation of an unswept wing in combination with a systematic series of four bodies
- Transonic wind-tunnel investigation of the effects of aspect ratio, spanwise variations in section thickness ratio, and a body indentation on the aerodynamic characteristics of a 45° sweptback wing-body combination
- Transonic wind-tunnel investigation of the effects of sweepback and thickness ratio on the wing loads of a wing-body combination of aspect ratio 4 and taper ratio 0.6
- Transonic wind-tunnel investigation of the interference between a 45° sweptback wing and a systematic series of four bodies
- Two-dimensional low-speed cascade investigation of NACA compressor blade sections having a systematic variation in mean-line loading
- Variation of peak pitching-moment coefficients for six airfoils as affected by compressibility
- Wind tunnel investigation of a plain aileron with various trailing-edge modifications on a tapered wing : 1- Aileron with fixed inset tabs
- Wind tunnel investigation of control surface characteristics : 12 - Various cover-plate alinements on the NACA 0015 airfoil with a 30 percent chord flap and large sealed internal balance
- Wind tunnel investigation of effect of yaw on lateral-stability characteristics : 4 - Symmetrically tapered wing with a circular fuselage having a wedge-shaped rear and a vertical tail
- Wind-tunnel investigation at high subsonic speeds of the effect of spoiler profile on the lateral control characteristics of a wing-fuselage combination winter quarter-chord line swept back 32.6° and NACA 65A006 airfoil section
- Wind-tunnel investigation at high subsonic speeds to determine the rolling derivatives of two wing-fuselage combinations having triangular winds, including a semiempirical method of estimating the rolling derivatives
- Wind-tunnel investigation at low speed of the effect of varying the ratio of body diameter to wing span from 0.1 to 0.8 on the aerodynamic characteristics in pitch of the 45° sweptback-wing--body combination
- Wind-tunnel investigation of a revised horizontal tail surface for the Grumman TBF-1 airplane
- Wind-tunnel investigation of damping in roll at supersonic speeds of triangular wings at angles of attack
- Wind-tunnel investigation of effect of sweep on rolling derivatives at angles of attack up to 13° and at high subsonic Mach numbers, including a semiempirical method of estimating the rolling derivatives
- Wind-tunnel investigation of shielded horn balancees and tabs on a 0.7-scale model of XF6F vertical tail surface
- Wind-tunnel investigation of the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4
- Wind-tunnel investigation of the effect of aspect ratio and chordwise location on effectiveness of spoiler-slot-deflector controls on thin untapered winds at transonic speeds
- Wind-tunnel investigation of the effects of steady rolling on the aerodynamic loading characteristics of a 45° sweptback wing at high subsonic speeds
- Wind-tunnel investigation of the effects of various dorsal-fin and vertical-tail configurations on the directional stability of a streamlined body at transonic speeds, transonic-bump method
- Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds : Aspect-ratio series
- Wind-tunnel tests of a blunt-nose aileron with beveled trailing edge on an NACA 66(215)-216 airfoil with several modification of aileron nose and adjacent airfoil contour

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