COMPUTATION OF AERODYNAMIC CHARACTERISTICS AND NONLINEAR STABILITY DERIVATIVES OF A FIGHTER/ATTACK AIRCRAFT AT HIGH ANGLES OF ATTACK

MODERN TACTICAL AIRCRAFT FLYING AT HIGH ANGLES OF ATTACK ENCOUNTER VISCOUS SEPARATION, VORTEX FLOWS, VORTEX BREAKDOWN, UNSTEADY FLOW SITUATIONS AND THEIR EFFECTS ON THE LIFTING SURFACES DOWNSTREAM. IT IS VERY IMPORTANT TO ANALYZE THESE FLOWS IN ORDER TO PREDICT THE STABILITY DERIVATIVES ACCURATELY AND ALSO IT IS HIGHLY DESIRABLE THAT IN THE METHODS PREDICTING THE STABILITY DERIVATIVE OF THESE AIRCRAFTS AS MANY OF THESE PHENOMENA ARE INCLUDED TO REDUCE COSTLY WIND TUNNEL TESTS AND FLIGHT TESTS. HERE IT IS PROPOSED TO DEVELOP A COMPUTER PROGRAM TO PREDICT LONGITUDINAL AND LATERAL-DIRECTIONAL STABILITY DERIVATIVES OF A FIGHTER/ATTACK AIRCRAFT AT HIGH ANGLES OF ATTACK.