Aeroheating Testing and Predictions for Project Orion Crew Exploration Vehicle

摘要

An investigation of the aeroheating environment of the Project Orion Crew Exploration Vehicle was performed innthe Arnold Engineering Development Center Hypervelocity Wind Tunnel 9 Mach 8 and Mach 10 nozzles and in thenNASA Langley Research Center 20-Inch Mach 6 Air Tunnel. Heating data were obtained using a thermocoupleinstrumentednu00010:035-scale model [0.1778 m (7 in.) diameter] of the flight vehicle. Runs were performed in thenTunnel 9 Mach 10 nozzle at freestream unit Reynolds numbers of 1 u0002 106 to 20 u0002 106=ft, in the Tunnel 9 Mach 8nnozzle at freestream unit Reynolds numbers of 8 u0002 106 to 48 u0002 106=ft, and in the 20-Inch Mach 6 Air Tunnel atnfreestream unit Reynolds numbers of 1 u0002 106 to 7 u0002 106=ft. In both facilities, enthalpy levels were low and the test gasn(N2 in Tunnel 9 and air in the 20-Inch Mach 6 Air Tunnel) behaved as a perfect gas. These test conditions producednlaminar, transitional, and turbulent data in the Tunnel 9 Mach 10 nozzle; transitional and turbulent data in thenTunnel 9 Mach 8 nozzle; and laminar and transitional data in the 20-Inch Mach 6 Air Tunnel. Laminar and turbulentnpredictions were generated for all wind-tunnel test conditions, and comparisons were performed with thenexperimental data to help define the accuracy of the computational method. In general, it was found that bothnlaminar data and predictions and turbulent data and predictions agreed to within less than the estimated u000312%nexperimental uncertainty estimate. Laminar heating distributions from all three data sets were shown to correlatenwell and demonstrated Reynolds numbers independence when expressed in terms of the Stanton number based onnadiabatic-wall-recovery enthalpy. Transition-onset locations on the lee-side centerline were determined from thendata and correlated in terms of boundary-layer parameters. Finally, turbulent heating augmentation ratios werendetermined for several body-point locations and correlated in terms of the boundary-layer momentum Reynoldsnnumber.