Abstract
This paper presents methodology of spin analysis of a multirole fighter aircraft, in open loop configuration, having aerodynamic asymmetry in yawing moment at high angles of attack. High fidelity aerodynamic model is developed in the form of lookup tables from static, coning and oscillatory coning test data obtained from Rotary Balance wind tunnel tests. Steady spin modes are predicted by solving 3-DOF aircraft model in conjunction with developed aerodynamic model using Nelder-Mead Simplex Optimization Routine. The natural tendency of an aircraft to yaw to the right at high angles of attack has resulted in prediction of significantly higher number of right spins as compared to left spins. 6-DOF time history simulations performed from selected initial conditions of steady spins showed that flat spins, both right and left are oscillatory and unstable. Proposed spin recovery strategies using aerodynamic control surfaces are found to accelerate spin recovery of left flat spins. However right flat spins which span across the whole range of aileron and elevator deflections do not respond to attempted recovery actions.
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