Abstract: A shock tube can be used as a convenient aerodynamic testing facility. Thus it was extensively applied to experimental research of transonic and hypersonic flow. However, due to its very short working time quantitative flow measurement such as pressure distribution around a model installed in the shock tube is very difficult. This paper reports the results of unsteady pressure distribution and unsteady drag measurement over circular cylinder installed in a 50mm × 200mm shock tube equipped with Mach-Zehnder ...