Flight-test base pressure measurements in turbulent flow
Flight-test base pressure data obtained from relatively sharp (5 to 6 percent nose bluntness), slender (9-degree half angle) conical reentry vehicles are discussed. The measurements are presented as a function of Mach number to emphasize base pressure variations throughout the range M/sub infinity/ = 0.5 to 15 in turbulent boundary-layer flow conditions. A satisfactory data correlation is developed in terms of local cone parameters to assess the sensitivity of base pressure to nose bluntness and cone angle for vehicles characterized by very low heatshield ablation rates (mass addition parameter m-dot/rho/sub infinity/ V/sub infinity/A/sub B/ less than 0.001). Comparisons of experimental pressure coefficient (base drag) with limited numerical solutions are included. 5 figures.
- Research Organization:
- Sandia Labs., Albuquerque, N.Mex. (USA)
- DOE Contract Number:
- AT(29-1)-789
- OSTI ID:
- 7361503
- Report Number(s):
- SAND-76-0267
- Country of Publication:
- United States
- Language:
- English
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