Results 141 to 150 of about 845 (188)

The Airworthiness of Supersonic Aircraft

Aircraft Engineering and Aerospace Technology, 1969
IF the history of air transport is traced back we find that superimposed on a steady rate of development, there have been several important milestones standing out as major jumps in technological progress. The first cabin airliner‐the first monoplane‐the first pressure cabin‐the first turbine‐the first jet and now the first supersonic transport.
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Supersonic STOVL Research Aircraft

SAE Technical Paper Series, 1982
<div class="htmlview paragraph">Two powered-lift concepts, the tandem fan and the longitudinally-arrayed ejector, are integrated with two existing fighter aircraft, the F-l4A and F-16A respectively, to indicate the benefits and/or penalties involved with providing STOVL capability to CTOL aircraft.
Samuel B. Wilson, George H. Kidwell, George E. Turney, Al Rogers   +3 more
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Supersonic combat aircraft design

The Aeronautical Journal, 1979
It should be fairly obvious that, in contemplating the design of a future combat aircraft, it is important at the outset to relate the effort to some forecast definition of what is needed. This may take the form of an official or an unofficial requirement; however, its precise form is immaterial to the central argument.
J. FLETCHER, B. BURNS
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Range optimization for a supersonic aircraft

Navigation and Control Conference, 1991
Range optimal trajectories for an aircraft flying in the vertical plane are obtained from Pontryagin's Minimum Principle. Control variables are load factor n which appears nonlinearly in the equations of motion and throttle setting eta, which appears only linearly.
HANS SEYWALD, EUGENE CLIFF, KLAUS WELL
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Engineering Systems on Supersonic Aircraft

The Journal of the Royal Aeronautical Society, 1961
A great deal has been said and written about the necessity to launch into a completely new standard plateau of systems engineering for supersonic, as distinct from subsonic, aircraft. So far as I have been able to gather, one reason for all this could be the argument that, as the supersonic aircraft will be so costly to operate, i.e.
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Supersonic aircraft drag reduction

21st Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1990
This paper reviews aerodynamic drag reduction for friction, wave and vortex drag associated with supersonic cruise aircraft and suggests approaches and research directions. Suction laminar flow control may also enable improved low-speed, high-lift systems, improved lift-to-drag ratio for subsonic cruise, reduced parasitic viscous drag for favorable ...
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Multilevel optimization of a supersonic aircraft

Finite Elements in Analysis and Design, 2004
This paper investigates the application of a multilevel preconditioned algorithm for the sonic boom reduction of a supersonic business jet. The optimization algorithm relies on a gradient approach with an adjoint state evaluation. The multi-level preconditioner is designed from an analysis of the gradient regularity loss.
Koobus, Bruno, Vazquez, Mariano, Dervieux, Alain   +2 more
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Exhaust Nozzles For Supersonic Aircraft

The Journal of the Royal Aeronautical Society, 1958
The Ordinary convergent exhaust nozzle is a perfectly satisfactory and efficient device for converting pressure in the jet pipe into velocity, so long as the pressure ratio across it remains below about 2.0; or, put another way, so long as the velocity at exit from the nozzle is not theoretically greater than that of sound at the jet temperature ...
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The Navigation and Control of Supersonic Aircraft

Journal of Navigation, 1962
This paper, which was presented at an Ordinary Meeting of the Institute held in London on 17 November 1961, discusses aspects of high-speed, high-altitude navigation which will have a bearing on the selection of a navigation system and control philosophy for supersonic transports.
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Drag Analysis of a Supersonic Fighter Aircraft

2016
For aircraft design, drag optimization is very important for having better flight performance and less fuel consumption. In this study, drag effects of fuselage, wing and tail section are separately analyzed using a generic F-16 fighter aircraft model in ANSYS Fluent CFD tool with polyhedral mesh.
Kurtulus D. F., Golcuk A. I., Akgun O., Kaynak Ünver   +3 more
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