Computation of transonic flows past lifting airfogs and slender bodies

Abstract

Solutions of the transonic small disturbance equation are presented for flow past thin lifting airfoils and slender bodies with M∞ < 1, including cases with imbedded shock waves. The results are obtained numerically using a mixed finite-difference relaxation method previously reported by the authors. Results are presented for four lifting airfoils at various angles of attack and are compared with shock free theory and experimental data. For the slender body case, comparisons with experiments are given for five geometries both with and without aft stings. The results are also compared with approximate theory. Discussion is given on the treatment of the boundary conditions, computing times and accuracies, and ranges of applicability of the small disturbance theory. © 1972 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.