Effect of tunnel noise on laminar stagnation-point heating at mach 6
Abstract
Accurate knowledge of heat transfer is essential for the safe and efficient design of hypersonic vehicles. Many uncertainties are associated with heat transfer measurements in wind tunnels, including the effect of tunnel noise. Heat transfer measurements were made in the Boeing/AFOSR Mach-6 Quiet Tunnel to characterize the potential for noise to affect stagnation-region heating on blunt bodies. Of particular interest were the blunt stagnation regions of hemispheres and the Crew Exploration Vehicle forebody heat shield. Heat flux was measured using coaxial thermocouples and Schmidt-Boelter gages and was then compared to results from a compressible boundary layer similarity solution. A comparison of data to computations revealed negligible differences between quiet and noisy-flow cases for the hemispheres. The CEV model did not start in noisy flow and the quality of flow under quiet conditions was questionable. Efforts were made to start the CEV by reconfiguring diffuser-section inserts and model streamwise location. These have not yet been successful.
Degree
M.S.E.
Advisors
Schneider, Purdue University.
Subject Area
Aerospace engineering
Off-Campus Purdue Users:
To access this dissertation, please log in to our
proxy server.