Measurement of shock-wave/boundary-layer interaction in a free-piston shock tunnel

The interaction between shock waves and boundary layers existing about a hypersonic vehicle is studied through shock tunnel experiments. Tests are carried out in a free-piston shock tunnel wherein a flat plate with a sharp leading edge is subjected to a simulated shock wave. The plate's pressure responses are then measured using an array pressure transducers and a digital event recorder. Results show that free-piston shock tunnels are useful for the speedy analysis of hypersonic shock-wave/boundary-layer interactions.