Comparisons of computed and experimental pressures for transonic flows about isolated wings and wing fuselage configurations

摘要

A relaxation procedure is presented for solving the transonic small disturbance equation for flows about wings and wing-fuselage combinations. The numerical method is based on the relaxation method of Murman and Cole and is a continuation of the work given by Ballhaus and Bailey. The small disturbance formulation is chosen because of the simple manner in which the wing boundary condition is imposed. All transonic relaxation methods for wings are based on the small disturbance approach. Solutions were obtained over a sequence of successively refined computational grids with the final result obtained for a grid with about 100,000 points. The solution process requires about 5 to 15 min of run time on a CDC 7600 computer.