| 摘要 |
A device for yawing moment control in aircraft with a slender nose at high angles of attack in the range of 20 DEG -80 DEG , most importantly 35 DEG -70 DEG , at speeds especially up to Mach 0.5, for elimination of stochastically arising asymmetrical body nose air vortices, characterized by ports arranged at both sides of the nose, which ports are mutually so connected that a pressure difference between the two sides produced by the symmetrical body nose air vortices is equalized. The device causes self-stabilizing of an aircraft at an oblique relative wind angle of up to about 5 DEG and a restoring yaw moment within the range of about 5 DEG -12 DEG . |
