Wall interference correction of wind tunnel experiment plays a very important role in assessing the validation of Computational Fluid Dynamics (CFD) and aircraft design. In this paper, based on an optimization formulation, a procedure has been developed to evaluate Mach number and angle-of-attack corrections for transonic wall interference problems. The Reynolds-averaged Navier-Stokes (RANS) equations are assumed to be the flow governing equations, and the gradient information for optimization is obtained by automatic differentiation method. The measured pressure distribution over the test model surface in experiment is used here. The Mach number and angle-of-attack are automatically updated to minimize the error between the measured and calculated pressure distributions. The corrections with present approach have been compared with the results of the lift interference correction method and the Barnwell-Sewall correction method. It has been proven that the corrected results using present method agree better to the experimental data, especially for the Shockwave position. With the corrected Mach number and angle-of-attack, the pressure distribution and aerodynamic coefficients such as lift coefficient and momentum coefficient are also proved to be more accurate with respect to the measured experimental values.
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