Aerodynamic characteristics of a deltawing in the case of harmonic oscillations with respect to the roll and yaw angles at high angles of attack

The aerodynamic characteristics of a delta wing in the case of harmonic oscillations with respect to the roll and yaw angles are obtained in a subsonic low-speed wind tunnel and analyzed. It is shown that at near-critical angles of attack the aerodynamic derivatives of the roll moment considerably depend on the reduced oscillation frequency. It is established that this dependence is due to a variation in the slip angle. A mathematical model that involves an ordinary linear differential first-order equation is used to describe the aerodynamic characteristics of the wing for the problems of aircraft flight dynamics at high angles of attack.