Convective heat-transfer rates on large-angle conical bodies at hypersonic speeds
Convective heat transfer rates on large angle conical bodies at hypersonic speeds
Marvin, J. G.↗
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Theoretical Stability Derivatives for the X-15 Research Airplane at Supersonic and Hypersonic Speeds Including a Comparison with Wind-tunnel Results
Longitudinal and lateral stability and control derivatives for X-15A aircraft at supersonic and hypersonic speeds - comparison of theoretical results with wind tunnel testing
LATERAL STABILITY AND CONTROL↗
A modified-strip-analysis method for predicting wing flutter at subsonic to hypersonic speeds
Modified strip analysis method for predicting wing flutter at subsonic to hypersonic speeds
AERODYNAMIC FORCE↗
Variational approach to conical bodies having maximum lift-to-drag ratio at hypersonic speeds.
Variational approach to conical bodies having maximum lift drag ratio at hypersonic speeds, assuming Newtonian pressure distribution and constant friction coefficient
Huang, H.-Y.↗
Linearized theory of stagnation region skin friction and mass transfer at hypersonic speeds
Linearized theory of stagnation region skin friction and mass transfer at hypersonic speeds
Yoshikawa, K. K.↗
EFFECT OF SURFACE DISTORTIONS ON THE HEAT TRANSFER TO A WING AT HYPERSONIC SPEEDS
Effects of surface distortions on the heat transfer and surface pressure on a wing at hypersonic speeds
HYPERSONIC BOUNDARY LAYER↗
Conical bodies of given length and volume having maximum lift-to-drag ratio at hypersonic speeds - Direct methods
Lift to drag ratios of slender, conical bodies flying at hypersonic speeds, and effects of geometric parameters on aerodynamic stability
Heideman, J. C.↗
A general theory of the development of finite-amplitude disturbances in the unstable laminar wake behind plane bodies at hypersonic speeds.
Finite amplitude disturbance development in unstable laminar wake behind plane bodies at hypersonic speed described by generalized theory
Liu, J. T. C.↗
Improvement of wing-body interference theory for hypersonic speeds
Wing-body interference theory for calculating lift slope and stability at hypersonic speed
Pitts, W. C.↗
EFFECTS OF MASS ADDITION ON THE STABILITY OF SLENDER CONES AT HYPERSONIC SPEEDS
Effects of gas injection on the heat transfer and pressure distributions on slender cones at hypersonic speeds
HEAT TRANSFER↗
Conical bodies of given length and volume having maximum lift-to-drag ratio at hypersonic speeds. II - Variational methods.
Lift to drag ratio by slender conical body flying at hypersonic speeds
Huang, H.-Y.↗
Linearized Theory of Stagnation Point Heat and Mass Transfer at Hypersonic Speeds
Solution for shock layer energy equation with mass and convective heat transfer at hypersonic speed
Yoshikawa, Kenneth K.↗
Optimum transversal contour of a lifting body at hypersonic speeds.
Lift drag ratio attainable by optimal transversal contour slender conical lifting body at hypersonic speeds
Miele, A.↗
Blast-wave correlation of pressures on blunt- nosed cylinders in perfect- and real-gas flows at hypersonic speeds.
Blast-wave correlation of pressures on blunt-nosed cylinders in perfect and real-gas flow at hypersonic speeds
SHOCK WAVE↗
Theoretical and experimental longitudinal aerodynamic characteristics of an aspect ratio 0.25 sharp-edge delta wing at subsonic, supersonic, and hypersonic speeds
The suction analogy concept of Polhamus for predicting vortex lift in conjunction with an appropriate potential-flow solution is called the present method. This method is applied to an aspect ratio 0.25 sharp-edge delta wing from a Mach number of 0.143 to 10.4 in free air and at 0.074 in ground effect, and also to an aspect ratio 0.35 triangular crosssectional body at a Mach number of 6.9. The models had subsonic leading edges at the test Mach numbers. Vortex-flow effects could be neither confirmed nor denied to exist at high speeds because of the lack of flow visualization above a Mach number of 0.143. The data, however, could be better predicted by including a vortex-flow effect, although not always to the extent predicted from the present method because of the presence of actual and hypothesized unmodeled flow situations. The method of Nenni and Tung (NASA CR-1860) tended to confirm the existence of vortex flow at hypersonic speeds. The hypersonic-tangent-cone method predicted best the delta-wing results over the test angle-of-attack range and hypersonic Mach number range and did equally as well as the present method for the triangular body.
Fox, C. H., Jr.↗
Convective heat-transfer rates on a blunted 110 deg cone with hemispherical afterbody at hypersonic speeds
Measurement of convective heat transfer rates on conical nosecap and hemispherical afterbody configuration at hypersonic speed
Stewart, D. A.↗
Time dependent shear stress and temperature distribution over an insulated flat plate moving at hypersonic speed.
The laminar two-dimensional flow over a stepwise accelerated flat plate moving with hypersonic speed at zero angle of attack is analysed. The governing equations in the self-similar form are linearized and solved numerically for small times. The solutions obtained are the deviations of the velocity and the temperature profiles from those of steady state. The presented results may be used to find the first order boundary layer induced pressure on the plate.
Rodkiewicz, C. M.↗
Aerodynamic testing technique for twin fuselage models at hypersonic speeds
A testing technique for obtaining the static aerodynamic characteristics of twin-fuselage configurations at hypersonic speeds by using a conventional single-balance installation has been evaluated. Data from a triple-fuselage model and a single-fuselage model were summed and then halved to obtain the characteristics for a twin-fuselage model of the same scale. The three related models were evaluated experimentally at Mach 20.3 in helium and Mach 6 in air for an angle-of-attack range from minus 6 deg to 50 deg. The Reynolds numbers, based on model length, were 1.88 million for the Mach 20.3 tests and 2.55 million for the Mach 6 tests.
Ashby, G. C., Jr.↗