Efforts Towards Shear Stress and Heat Flux Measurement On a Hollow Cylinder at Mach 6

Shear stress and heat-flux surface quantities were measured on a fully-turbulent hollow cylinder at Mach 6 using shear stress sensors and temperature gauges. Experiments were conducted at the Stevens Shock Tunnel (SST) with a ‘flight-enthalpy-matched’ and a ‘cold-flow’ condition. Heat flux was recovered from temperature gradients using both the Cook-Felderman 1-D semi-infinite heat flux equation and an inverse FFT solution using Green’s function. Temperature gauges were capable of recording µs level effects in the flow. Non-dimensionalising the recovered heat flux to Stanton Number vs Reynolds number shows 50% undershoot to the value theorized by correlations for turbulent flow conditions. In the future, the method of Whalen et al. [1] will be used to correct for errors associated with the sensing element being of finite depth. Wall shear sensor signal only exceeded the noise floor for the enthalpy-matched condition. Both measurements were non-dimensionalized to Stanton number and compared to correlations well documented in literature.