Abstract: Using pointed tangent-ogive slender body,under the Mach number ranged from 0.4 to 1.2,and angle of attack ranged from 0°to 50°,the pressure measure tests and PIV tests were completed in high speed wind tunnel to investigate the response between model tip perturba-tion and asymmetric vortex flow at high angles of attack.The results show that asymmetric multi-vortex flow structures still exist in high speed case.It was observed that there was a distinct relation between tip perturbation and response of asymmetric vortex flow,but a feeble relation between tip perturbation and response of asymmetric aerodynamic force.