Boundary layer transition at hypersonic conditions is critical to the design of future high-speed aircraft and spacecraft. Accurate methods to predict transition would directly impact the aerothermodynamic environments used to size a hypersonic vehicle's thermal protection system. A transition prediction tool, based on wind tunnel derived discrete roughness correlations, was developed and implemented for the Space Shuttle return-to-flight program. This tool was also used to design a boundary layer transition flight experiment in order to assess correlation uncertainties, particularly with regard to high Mach-number transition and tunnel-to-flight scaling. A review is provided of the results obtained from the flight experiment in order to evaluate the transition prediction tool implemented for the Shuttle program.
Flight Experiment Verification of Shuttle Boundary Layer Transition Prediction Tool
2016
16 pages
Report
Keine Angabe
Englisch
Fluid Mechanics , Space shuttles , Spacecraft reentry , Hypersonic speed , Hypersonic boundary layer , Boundary layer transition , Aerothermodynamics , Thermal protection , Temperature control , Control systems design , Surface roughness effects , Aerodynamic configurations , Flight tests , Prediction analysis techniques
Flight Experiment Verification of Shuttle Boundary Layer Transition Prediction Tool (AIAA 2016-3533)
British Library Conference Proceedings | 2016
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