An aeroelastic analysis method for fighter aircraft operating at extreme flight conditions has been developed and tested. The method involves the use of state-of-the-art zonal grid generation methods, three-dimensional Reynoldsaveraged Navier-Stokes analysis, and linear structures to analyze the flow over complex, flexible aircraft. The main objective of this effort is to develop a method capable of analyzing aircraft operating at flight conditions where vortices, strong shock waves, separated flow, and even highly unsteady flow may be present. The present application focuses on the static aeroelastic analysis of fighter aircraft operating at high angle of attack and high transonic Mach number. The developed method has been compared against static aeroelastic wind-tunnel data on an aeroelastically tailored wing/fuselage configuration, and the results are very encouraging.
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