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.
Application of Fast Pressure Sensitive Paint in Hypervelocity Flow
The development of fast responding pressure sensitive paints for measurements in high-enthalpy, hypersonic flows is reported. Data are obtained for at plate boundary layers in 
an impulse facility with typical test gas times on the order of hundreds of microseconds. 
The fast pressure sensitive paint is found to have the required response time and sufficient 
signal level to visualize vortical boundary layer structures in a Mach 5.12 freestream. The 
flow behind protuberance strips with different geometries is evaluated with measurements 
of the vortex frequency and diameter, as well as breakdown distance. Comparisons with 
static pressure measurements made using pressure taps show differences of up to a factor 
of three, and calibration sources as well as an alternative lifetime measurement method 
remain to be investigated.
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 (ﬂat 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.