#
Aerodynamics, Supersonic
Resource Information
The concept ** Aerodynamics, Supersonic** represents the subject, aboutness, idea or notion of resources found in **University of Oklahoma Libraries**.

The Resource
Aerodynamics, Supersonic
Resource Information

The concept

**Aerodynamics, Supersonic**represents the subject, aboutness, idea or notion of resources found in**University of Oklahoma Libraries**.- Label
- Aerodynamics, Supersonic

- Authority link
- http://id.worldcat.org/fast/00798221

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- fast

## Context

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- Wind-tunnel investigation of the static longitudinal and lateral stability of a 1/62-scale model of the X-1E at supersonic speeds
- A Method for determining the aerodynamic characteristics of two- and three-dimensional shapes at hypersonic speeds
- A System for aerodynamic design and analysis of supersonic aircraft
- A combined aerodynamic and guidance approach for a simple homing system
- A method for designing low-drag nose-inlet-body combinations for operation at moderate supersonic speeds
- A pivoting-cowl-and-spike technique for efficient angle-of-attack operation of supersonic inlets
- 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 study of the sonic-boom characteristics of a blunt body at a Mach number of 6
- A wind-tunnel test technique for measuring the dynamic rotary stability derivatives including the cross derivatives at high Mach numbers
- 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 a supersonic fighter aircraft model at Mach 0.40 to 2.47
- Aerodynamic characteristics over a Mach number range of 1.40 to 2.78 of a rocket-propelled airplane configuration having a low 52.2Â° delta wing and an unswept horizontal tail
- Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5
- Airplane motions and loads induced by flying through the flow field generated by an airplane at low supersonic speeds
- An Experimental investigation of the effect of surface heating on boundary-layer transition on a flat plate in supersonic flow
- 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 of a supersonic aircraft configuration having a tapered wing with circular-arc sections and a 40Â° sweepback : pressure distribution measurements of the interference effect of the wing on the fuselage at Mach numbers of 1.40 and 1.59
- Analytical investigation of fuel temperatures and fuel-evaporation losses encountered in long-range high-altitude supersonic flight
- Application of oblique-shock sensing system to ram-jet-engine flight Mach number control
- Applications of Von Karman's integral method in supersonic wing theory
- Approximate solutions for the flow about flat-top wing-body configurations at high supersonic airspeeds
- Average skin-friction coefficients from boundary-layer measurements on an ogive-cylinder body in flight at supersonic speeds
- Axisymmetric supersonic flow in rotating impellers
- Calculation of surface temperatures in steady supersonic flight
- Characteristics of a free supersonic helium jet issuing normally from a flat plate
- Combustion of aluminum borohydride in a supersonic wind tunnel
- Compilation and correlation of model starting loads from several supersonic wind tunnels
- Criteria for initial flow reversal in symmetrical twin-intake air-induction systems operating at supersonic speeds
- Damping in roll of cruciform and some related delta wings at supersonic speeds
- Development of flow distortions in a full-scale nacelle inlet at mach numbers 0.63 and 1.6 to 2.0
- Dynamics of a supersonic inlet with adjustable bypass in combination with a J34 turbojet engine
- Effect of aspect ratio on undamped torsional oscillations of a thin rectangular wing in supersonic flow
- Estimation of the static aerodynamic characteristics of ordnance projectiles at supersonic speeds
- Estimation of wing nonlinear aerodynamic characteristics at supersonic speeds
- Evaluation of five conical center-body supersonic diffusers at several angles of attack
- Experimental determination of damping in pitch of swept and delta wings at supersonic Mach numbers
- Experimental investigation of base pressure on blunt-trailing-edge wings at supersonic velocities
- Experimental investigation of temperature recovery factors on bodies of revolution at supersonic speeds
- Experimental pressure distributions over wing tips at Mach number 1.9, [Part] 2, Wing tip with subsonic trailing edge
- Factors affecting the maximum lift-drag ratio at high supersonic speeds
- Factors affecting transition at supersonic speeds
- Final design of Sandia's supersonic parachute test vehicle
- 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
- Flow over a slender body of revolution at supersonic velocities
- Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99, [Part] 2, Isentropic-spike all-external compression inlet
- 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
- Heat transfer to blunt nose shapes with laminar boundary layers at high supersonic speeds
- Heat-transfer characteristics of blunt two-and three-dimensional bodies at supersonic speeds
- High-speed computing machine calculation of supersonic axisymmetric flows
- Improvement of accuracy of balanced-pressure indicators and development of an indicator calibrating machine
- Investigation at supersonic and subsonic Mach numbers of auxiliary inlets supplying secondary air flow to ejector exhaust nozzles
- Investigation at supersonic speeds of the compressor stall and inlet buzz characteristics of a J34 - spike-inlet combination
- 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 of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study, [Part] I, Design and experimental performance of standard turbine
- 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 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 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 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 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 types of supersonic diffuser over a range of Mach numbers from 1.75 to 2.74
- 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
- Lee-side flow over delta wings at supersonic speeds
- Line-vortex theory for calculation of supersonic downwash
- Location of detached shock wave in front of a body moving at supersonic speeds
- Longitudinal aerodynamic characteristics of a model airplane configuration equipped with a scaled X-1 airplane wing
- Performance of external-compression bump inlet at Mach numbers of 1.5 to 2.0
- Preliminary attempts at isothermal compression of a supersonic air stream
- Pressure measurements on a body of revolution in the Langley 16-foot transonic tunnel and a comparison with free-fall data
- Rolling and yawing moments for swept-back wings in sideslip at supersonic sppeds
- Some effects of aircraft configuration on static longitudinal and directional stability characteristics at supersonic Mach numbers below 3
- Some effects of fin plan form on the static stability of fin-body combinations at Mach number 4.06
- Some internal-flow characteristics at zero flight speed of an annular supersonic inlet and an open-nose inlet with sharp and rounded lips
- 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 theoretical characteristics of trapezoidal wings in supersonic flow and a comparison of several wing-flap combinations
- Span loadings due to wing twist at transonic and supersonic speeds
- Stability derivatives of triangular wings at supersonic speeds
- 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
- Supersonic lift and pitching moment of thin sweptback tapered wings produced by constant vertical acceleration : Subsonic leading edges and supersonic trailing edges
- The Calculation of downwash behind supersonic wings with an application to triangular plan forms
- The effects of a small jet of air exhausting from the nose of a body of revolution in supersonic flow
- The proper combination of lift loadings for least drag on a supersonic wing
- The reversibility theorem for thin airfoils in subsonic and supersonic flow
- The static and dynamic longitudinal stability characteristics of some supersonic aircraft configurations
- The use of perforated inlets for efficient supersonic diffusion
- The yawing moment, due to sideslip of triangular, trapezoidal, and related plan forms in supersonic flow
- Theoretical lift and damping in roll of thin sweptback wings of arbitrary taper and sweep at supersonic speeds : Subsonic leading edges and trailing edges
- Theoretical loading at supersonic speeds of flat swept-back wings with interacting trailing and leading edges
- Theoretical prediction of the side force on stores attached to configurations traveling at supersonic speeds
- Theoretical relations between the stability derivatives of a wing in direct and in reverse supersonic flow
- Theoretical study of air forces on an oscillating or steady thin wing in a supersonic main stream
- Three-degree-of-freedom evaluation of the longitudinal transfer functions of a supersonic canard missile configuration including changes in forward speed
- Transient aerodynamic behavior of an airfoil due to different arbitrary modes of nonstationary motions in a supersonic flow
- Turbulent boundary-layer temperature recovery factors in two-dimensional supersonic flow
- Use of a characteristic surfaces for unsymmetrical supersonic flow problems
- Volterra's solution of the wave equation as applied to three-dimensional supersonic airfoil problems
- Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds : Aspect-ratio series

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