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Historically, the endeavor of scale testing flight vehicles at supersonic Mach numbers, especially for long durations, has required the development of closed-loop wind tunnels, which are extremely expensive both to build and operate due to the high complexity and incredible power required to drive such a system.
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Closure to “Discussions of ‘Supersonic Diffusers for Wind Tunnels’” (1949, ASME J. Appl. Mech., 16, pp. 417–418) [PDF]
E. P. Neumann, F. Lustwerk
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Supersonic wind tunnel nozzles: A selected, annotated bibliography to aid in the development of quiet wind tunnel technology [PDF]
This bibliography, with abstracts, consists of 298 citations arranged in chronological order. The citations were selected to be helpful to persons engaged in the design and development of quiet (low disturbance) nozzles for modern supersonic wind tunnels.
Wolf, Stephen W. D.
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Application of computational fluid dynamics and laminar flow technology for improved performance and sonic boom reduction [PDF]
A discussion is given of the many factors that affect sonic booms with particular emphasis on the application and development of improved computational fluid dynamics (CFD) codes.
Bobbitt, Percy J.
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RETALT: review of technologies and overview of design changes. [PDF]
Marwege A+13 more
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An experimental system for release simulation of internal stores in a supersonic wind tunnel
Wei Liu+7 more
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It is demonstrated that a supersonic airplane configuration weighing over half a million pounds while creating a maximum sonic boom of less than 1 p.s.f. can be designed.
Ting, L.
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Thermal Behavior of Carbon-Phenolic/Silica Phenolic Dual-Layer Ablator Specimens through Arc-Jet Tests. [PDF]
Chinnaraj RK, Kim YC, Choi SM.
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Radiative properties of advanced spacecraft heat shield materials [PDF]
Experimental results are presented to show the effects of simulated reentry exposure by convective heating and by radiant heating on spectral and total emittance of statically oxidized Inconel 617 and Haynes HS188 superalloys to 1260 K and a silicide ...
Cunnington, G. R.+2 more
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