Wind Tunnel Model Static Aeroelastic Deformation Correction Method Based on Grid Reconstruction

High aspect ratio swept wings are commonly designed in the modern commercial airliners to meet the requirements of long range and high speed. The wind tunnel test of an aircraft model in high-speed configuration has been conducted. The Reynolds number has been kept the same at the same Mach number while changing the dynamic pressure. Wind tunnel test results show that the deflection of the wingtip can reach 5% of the semi-wingspan, and the wingtip twist angle can reach − 3° at cruising Mach number. A wind-tunnel aircraft model static aeroelastic deformation correction method coupling Reynold-Averaged Navier-Stokes computation and grid reconstruction technology has been set up. The analysis results of the integral longitudinal coefficients validated against the wind tunnel experimental data indicate that the method presented can identify the differences in aerodynamic characteristics caused by deformation and dynamic pressure correctly. Pressure distributions including shock wave position and intensity vary with the free inflow dynamic pressure. The proposed correction method, which has been successfully applied to the aircraft engineering design, is regarded as a useful way to meet the design requirements.