Boundary layer trip devices for the Hper-X forebody have been experimentally examined in several wind tunnels. Five different trip configurations were compared in three hypersonic facilities, the LaRC 20-Inch Mach 6 Air Tunnel, the LaRC 31 -Inch Mach 10 Air Tunnel, and in the HYPULSE Reflected Shock Tunnel at GASL. Heat transfer distributions, utilizing the phosphor thermography and thin-film techniques, shock system details, and surface streamline patterns were measured on a 0.333-scale model of the Hyper-X forebody. Parametric variations include angles-of-attack of 0-deg, 2-deg, and 4-deg; Reynolds numbers based on model length of 1.2 to 15.4 million: and inlet cowl door simulated in both open and closed positions. Comparisons of transition due to discrete roughness elements have led to the selection of a trip configuration for the Hyper-X Mach 7 flight vehicle.
Hypersonic Boundary-Layer Trip Development for Hyper-X
18th Applied Aerodynamics Conference ; 2000 ; Denver, CO, United States
2000-08-10
Preprint
No indication
English
Hypersonic Boundary-Layer Trip Development for Hyper-X
AIAA | 2001
|Hypersonic boundary-layer trip development for Hyper-X
AIAA | 2000
|Hypersonic Boundary-Layer Trip Development for Hyper-X
NTIS | 2000
|SPECIAL SECTION: HYPER-X - Hypersonic Boundary-Layer Trip Development for Hyper-X
Online Contents | 2001
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