Abstract
Experimental and numerical studies of the laminar shock-wave/boundary-layer interaction occurring past a hollow cylinder flare model in a Mach 10 air flow at zero incidence were conducted. Flowfield density measurements were performed by detecting x-ray emissions from the gas produced by electron-beam impact. A solution was found to make these measurements possible near the model surface. Wall pressure and heat flux measurements have been performed. All of the experimental results are compared with numerical results obtained by using Navier-Stokes and direct simulation Monte Carlo solvers
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Schedule a callMore From: AIAA journal. American Institute of Aeronautics and Astronautics
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