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.
Falcon Hypersonic Technology Overview
AF = Air Force DARPA = Defense Advanced Research Projects Agency HiSTED = High Speed Turbine Engine Demo HCV = Hypersonic Cruise Vehicle HTV = Hypersonic Technology Vehicle MIPT = Materials Integrated Product Team RATTLRS = Revolutionary Approach To Time critical Long Range Strike RCCP = Reusable Combined Cycle Program SOTA = State of the Art SLV = Small Launch Vehicle TBCC = Turbine Based Combined Cycle
Investigations of dielectric gratings using electrodynamic models based on volume integral equations
Eigenmodes of planar and cylindrical dielectric gratings (DGs) and electromagnetic wave scattering from multiplayer DGs are investigated. The DG characteristics are calculated using numerical-analytical solution of integral equations (IEs).