Aerodynamic characteristics for a passenger aircraft model with harmonic oscillations on rolling and yawing angles at high angles of attack

Experimental values of complexes of aerodynamic derivatives were obtained in a wind tunnel and analyzed for subsonic flow of a passenger aircraft model with harmonic oscillations on the rolling and yawing angles. It was demonstrated that for near-critical angles of attack, the complexes of aerodynamic derivatives taken for rolling and yawing have a string dependency on the normalized oscillation frequency. It was proven that this dependency is driven by derivatives with respect to angular velocities and angular acceleration. A mathematical model for aerodynamic loads was developed; it can be applied for aircraft flight dynamic problems and has satisfactory approximation to experimental aerodynamic characteristics.