Pressure and heat transfer measurement of vane surface in short duration wind tunnel

Surface pressure and heat transfer measurements of an enlarged vane were conducted at engine's typical Reynolds numbers and pressure ratios. The pressure coefficients decreased and the lowest point of the suction surface moved backward with an increasing pressure ratio, while the Reynolds number had small effect on the surface pressure coefficients. With increase of the Reynolds number, the surface heat transfer coefficients rose, and the transition occurred earlier at suction surface. The pressure ratio mainly affected the heat transfer of suction surface. The transition occurred later when the pressure ratio increased in small Reynolds number state. When supersonic flow appeared at the suction's rear region in large Reynolds number state, the heat transfer coefficients at large pressure ratio were lower than those at small pressure ratio. The local adiabatic wall temperatures decreased with increase of pressure ratio. In the case of constant pressure ratio, the local adiabatic wall temperature of laminar flow was lower than that of turbulent flow.