In the real flight and wind tunnel testing of aircraft configuration with pointed nose slender,the coefficients of side force and yawing moment which are generated by high angle of attack are inconsistency,leading to difficulty for analyzing and using.In order to remove this difficulty,an experimental technique in which a micro-perturbation is attached on nose tip of model is suggested in wind tunnel testing for measuring side force and yawing moment.Based on this technique,an experimental study was conduct...