Real Gas Scale Effects on Hypersonic Laminar Boundary-Layer Parameters Including Effects of Entropy-Layer Swallowing
Final rept. 21 Mar-20 Oct 1974,
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pagination or Media Count:
Inviscid and viscous laminar boundary layer flow-field calculations under perfect gas hypersonic wind tunnel and equilibrium real gas flight conditions are presented for the windward centerline of the Rockwell International 139 Space Shuttle Orbiter at 30 deg angle of attack. Correlation parameters for laminar boundary-layer edge quantities and surface heat transfer are developed which properly account for entropy-layer-swallowing effects under both real and perfect gas conditions. A cursory examination of chemical nonequilibrium effects on the inviscid flow field based on oblique shock relaxation is presented. Some implications of the proposed correlation parameters on boundary-layer transition are discussed.
- Unmanned Spacecraft
- Spacecraft Trajectories and Reentry