Shock Tube Experiments on Heat Transfer at Generic Re-entry Bodies
Since the beginning of space exploration, there has been a lot of research conducted on heat generation at high flight Mach numbers in the upper atmosphere. Currently areas of special interest are: aerodynamics/thermodynamics and flight mechanics of slender re-entry vehicles. Especially problems concerning heat phenomena, i.e. behaviour of ablative materials and their influence on the signature and flight trajectory are open questions. Accurate information on surface heating of slender vehicles during the re-entry phase in the upper atmosphere at hypersonic speeds is crucial for the validation of the computing codes. These are applied for calculating the aerothermodynamics and related problems numerically, which have considerable influence on the bodies’ navigation and control simulation. The ISL high-energy shock tunnels are ideal tools to provide for the generic re-entry body under investigation at high re-entry Mach numbers (M10, M12, M14) and several flight altitudes, ranging from 50 to 70 km, heat transfer values which are used to prove the numerics applied: Bird’s DS2V software .
KeywordsMach Number Shock Tube Nozzle Exit Direct Simulation Monte Carlo Vibrational Temperature
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