Titlebook: Shock Waves @ Marseille I; Hypersonics, Shock T Raymond Brun,Lucien Z. Dumitrescu Conference proceedings 1995 Springer-Verlag Berlin Heidel

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BOON

Interference and Transient Effects on Compression Ramp Flows at Hypersonic Mach Numbersflow adjustment have been examined, and the development of criteria to predict separated flow establishment times discussed. During the initial experiments, nozzle exit compression waves were found to be a corrupting influence. Methods of detecting this interference, and its effects, have been assessed.

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Effects of Leading-Edge Bluntness on Control Flap Effectiveness at Hypersonic Speedsin a hypersonic gun tunnel facility at .. = 8.2 and ../. = 9.0 × 10.. The flow structure over a low aspect ratio flat plate with a full span trailing edge flap has been investigated using high speed Schlieren photography as well as surface pressure and heat transfer measurements.

Ovulation

The Boundary Layer on a Sharp Cone in High-Enthalpy Flowaminar layer, heat flux levels are higher in air than in nitrogen because of a larger heat release from oxygen recombination at the wall. By varying the specific reservoir enthalpy in air and N., and from measurements in CO., it is found that real-gas effects stabilize the boundary layer.

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Frequency-Range

978-3-642-78831-4Springer-Verlag Berlin Heidelberg 1995

patriot

Shock Tube Investigations of Combustion Phenomena in Supersonic FlowsA survey is given of recent combustion dynamics research using shock tubes. There are three different fields where phenomena in supersonic gas flows resulting from chemical heat release are of particular interest:

空氣傳播

和平主義者

A Life with Shock Waves (Ernst Mach Memorial Lecture)iscovered, which delays BL separation. Shock focusing, amplification, and stability were investigated; a “shock nozzle” was devised, and also an improved version of the spiral contraction. Recently, the author joined Prof. Raymond Brun’s Marseille team working on the development of a new Stalker-tub