An Automated Procedure for Computing the Three-Dimensional Transonic Flow over Wing-Body Combinations,Including Viscous Effects. Volume I. Description of Analysis Methods and Applications.

摘要

This report describes a numerical method to predict the detailed pressure distribution and force and moment results for wing-body combinations at transonic Mach numbers less than one. The resulting computer code has been developed with the intent of providing the user with an easy to use and reliable tool that produces the most accurate possible engineering predictions. In order to provide accurate surface pressure predictions on the wing, several additional features of the typical transonic flow field have been incorporated. These consist of the viscous displacement effect, local strong viscous interaction at the shock wave foot and at the trailing edge (including an approximate treatment of local shallow separations), and finally, the interaction effect of the fuselage.