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Low-cost open-source camera view splitter (quadscope) for flow diagnostics. [PDF]
HardwareXSahoo A, DeBoskey RD, Narayanaswamy V.
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Experimental boundary-layer edge Mach numbers for two space shuttle orbiters at hypersonic speeds
, 1972 G. C. Ashby
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Adding Value at Hypersonic Speed
45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2009In the test and evaluation (T&E) world, obtaining critical ground-test data requires that the effort be approached as a value-added task. By acquiring the ground-test data faster and cheaper, value is added to the overall flight system development program. At the Arnold Engineering Development Center (AEDC), a culture of maximizing the value of all T&E
Dusty Vaughn +2 more
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Phugoid oscillations at hypersonic speeds
AIAA Journal, 1965A theoretical analysis is made of the long-period (phugoid) oscillations of a lifting vehicle in hypersonic flight up to and including orbital speeds in any atmosphere. These oscillations correspond to a direct exchange between the kinetic energy and the potential energy along an oscillating flight path governed primarily by the trimmed steady-state ...
Laitone, E., Chou, Y. S.
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Plume effects at hypersonic speeds
1992A 7° semi-angle blunted cone has been tested at a Mach number of 8.2 in an intermittent hypersonic wind tunnel. The Reynolds number based on cone base-diameter was 2.8×105. The heat transfer rate distribution was measured along the cones surface and schlieren pictures were taken of the whole flow field.
J. L. Stollery +2 more
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Sublimation of graphite at hypersonic speeds
AIAA Journal, 1965In this paper, a new theoretical model is presented for the sublimation of graphite at hypersonic flight speeds. The aerothermochemical interactions between dissociated air and graphite are treated by means of a nine-component model, including O, O2, N, N2, CO, CO2, C, C3, and CN.
SlNCLAIRE M. SCALA, LEON M. GlLBERT
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Incipient separation on flared bodies at hypersonic speeds
The Aeronautical Journal, 1999AbstractThe aerodynamic effectiveness of a cylinder-flare body at zero incidence under laminar and turbulent boundary-layer conditions has been studied experimentally. Two nose geometries, namely a 10° half-angle sharp cone and a hemisphere, were used.
Kontis, Konstantinos, Stollery, JL
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