Abstract
To simulate the aerodynamic heating environment for a hypervelocity vehicle, various ground test facilities have been developed and constructed. An arc-heated wind tunnel is one of these facilities and features long operational time; thus the arc-heated wind tunnel has been used mainly for the development and evaluation of a thermal protection system for space transportation systems. Thus generated plasma flows can be employed for the experiments of aerodynamic heating and heat protection systems but also to reveal the physical phenomenon across a shock wave in a high-temperature plasma flow. In this chapter, a 20 kW-class arc-heated wind tunnel operated at Department of Aeronautics and Astronautics, Kyushu University is depicted and shock wave experiments in an arc-heated high-temperature flow are discussed.
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