The paper discusses the results of an experimental and numerical investigation of tangential slot injection film cooling with zero pressure gradients in subsonic boundary layers at freestream Mach numbers of 0.4, 0.6, and 0.8. The results are compared with the predictions obtained from a finite-difference boundary-layer program developed by NASA for slot injection into turbulent supersonic boundary layers. The two sets of results are found to compare favorably. The numerical results point to the existence of a unique relation between isothermal effectiveness and adiabatic effectiveness, thereby confirming the existence of similarity conditions for temperature and velocity profiles.
Investigation of slot cooling at high subsonic speeds
AIAA Journal ; 14
1976-07-01
Miscellaneous
No indication
English
Investigation of slot cooling at high subsonic speeds
AIAA | 1976
|Flight research at high subsonic speeds
Engineering Index Backfile | 1948
|The drag increase at high subsonic speeds
TIBKAT | 1954
|Improvement of Maneuverability at High Subsonic Speeds
NTIS | 1974
|