Abstract: An inviscid base pressure model for transonic turbine blade is presented It is shown that for a given back pressure the base pressure at the trailing edge and the profile toss of the blade are fixed and the base pressure can be calculated using an inviscid numerical scheme. A parametric study shows that positive curvature downstream of the throat is advantageous for generating less loss.An inviscid base pressure model for transonic turbine blade is presented It is shown that for a given back pressure the ba...