359 research outputs found
The present status and the future of missile aerodynamics
Some recent developments in the state of the art in missile aerodynamics are reviewed. Among the subjects covered are: (1) tri-service/NASA data base, (2) wing-body interference, (3) nonlinear controls, (4) hypersonic transition, (5) vortex interference, (6) airbreathers, supersonic inlets, (7) store separation problems, (8) correlation of missile data, (9) CFD codes for complete configurations, (10) engineering prediction methods, and (11) future configurations. Suggestions are made for future research and development to advance the state of the art of missile aerodynamics
Analysis of the High-Altitude Cooling of the Ranger SGV-770 D-4 Engine in the Bell XP-77 Airplane
No abstract availabl
Quasi-cylindrical theory of wing-body interference at supersonic speeds and comparison with experiment
A theoretical method is presented for calculating the flow field about wing-body combinations employing bodies deviating only slightly in shape from a circular cylinder. The method is applied to the calculation of the pressure field acting between a circular cylindrical body and a rectangular wing. The case of zero body angle of attack and variable wing incidence is considered as well as the case of zero wing incidence and variable body angle of attack. An experiment was performed especially for the purpose of checking the calculative examples
Effect of aspect ratio and taper on the pressure drag at supersonic speeds of unswept wings at zero lift
Compressibility Effects on Heat Transfer and Pressure Drop in Smooth Cylindrical Tubes
An analysis is made to simplify pressure-drop calculations for nonadiabatic and adiabatic friction flow of air in smooth cylindrical tubes when the density changes due to heat transfer and pressure drop are appreciable. Solutions of the equation of motion are obtained by the use of Reynolds' analogy between heat transfer and skin friction. Charts of the solutions are presented for making pressure-drop calculations. A technique of using the charts to determine the position of a normal shock in a tube is described
The Effects of Body Vortices and the Wing Shock-expansion Field on the Pitch-up Characteristics of Supersonic Airplanes
General theory of wave-drag reduction for combinations employing quasi-cylindrical bodies with an application to swept-wing and body combinations
Tables of characteristic functions for solving boundary-value problems of the wave equation with application to supersonic interference
Wing-body interference at supersonic speeds with an application to combinations with rectangular wings
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