Technique for experimental determination of the total thrust-aerodynamic characteristics of aircraft models

A method of experimental determination of the force characteristics of nozzles (thrust, lift, and pitching moment) simultaneously with the aerodynamic characteristics of an aircraft model in a supersonic flow in proposed. The tests were conducted for a special methodical model, with equilibrium of the thrust and drag jorces being reached. It is shown that the internal force characteristics of the nozzle and the drag of the model, as well as the effective lift and pitching moment (with account of propulsion), can be determined from the measured thrust of the propulsion simulator.