Effect of Concave Wall Geometry on Heat Transfer in Hypersonic Boundary Layers
Heat transfer measurements are made to investigate the effects of concave surface curvature on a high-stagnation enthalpy boundary layer in a Mach 5.1 flow. Experiments are 
carried out using two curved models with 16 and 25 degree turning angles, and baseline 
planar models (at plate and linear ramp) for comparative study. Streamwise and spanwise 
cross-sections are obtained. Significant destabilization of the boundary layer is observed 
over the adverse pressure gradient geometries. For the curved surfaces, the heat flux distribution appears to exhibit a quadratic dependence with streamwise distance, in contrast 
with the linear dependence observed on the linear ramp.
YIP-08 Hypervelocity Boundary Layer Studies for Axisymmetric
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Advanced Hypersonic Test Facilities
Hypersonic Ground Test Requirements Principles of Hypersonic Test Facility Development NASA's HYPULSE Facility at GASL The LENS I and II Hypervelocity Tunnels and Application to Hypersonic Vehicle Testing Under Fully Duplicated Flight Conditions The U-12 Large Shock Tube Detonation-Driven Shock Tubes and Tunnels Aerothermodynamics Research in the DLR High Enthalpy Shock Tunnel HEG Characteristics of the HIEST and its Applicability for Hypersonic Aerothermodynamic and Scramjet Research Piston Gasdynamic Units with Multicascade Compression Arc-Heated Facilities The SCIROCCO 70-MW Plasma Wind Tunnel Aerodynamic and Propulsion Test Unit Arc-Heated Facilities (LBK) as a Tool to Study Aerothermodynamic Problems of Reentry Vehicles The NASA Langley Research Center 8-ft High Temperature Tunnel NASA Glenn Research Center's Hypersonic Tunnel Facility The ONERA F4 High-Enthalpy Wind Tunnel The AEDC Hypervelocity Wind Tunnel 9 A Hypersonic Ground-Test Facility Using Magnetic Levitation and Electromagnetic Propulsion Recent Increases in Hypersonic Test Capabilities at the Holloman High Speed Test Track and Design of a Magnetically Levitated Test Track Capability Increased Launching Capabilities at AEDC's Range/Track G A New Mach 8-15 True Temperature Test Facility Concept to Meet the U.S. Shortfall in Hypersonic Test Capability New-Generation Hypersonic Adiabatic Compression Facilities with Pressure Multipliers