Pressure-gradient effects on hypersonic turbulent skin friction and boundary-layer profiles.Local skin friction, total-temperature profiles, and pitot-pressure profiles were measured on the wall of a Mach-7.4 wind tunnel. The wall to adiabatic wall temperature ratio was varied from 0.3 to 0.5. Boundary-layer characteristics were compared with those predicted by a finite-difference method. Local skin friction was predicted to within 15%. Pressure-gradient effects on the temperature and Mach number distributions and the shape factor (displacement thickness/momentum thickness) were underpredicted, but the velocity distributions were closely predicted.
Document ID
19720034257
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hopkins, E. J.
Keener, E. R. (NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 6, 2013
Publication Date
January 1, 1972
Subject Category
Fluid Mechanics
Report/Patent Number
AIAA PAPER 72-215
Meeting Information
Meeting: American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting