An Automated Procedure for Computing the Three-Dimensional Transonic Flow Over Wing-Body Combinations, Including Viscous Effects. Volume II. Program User's Manual and Code Description.

摘要

This volume provides the detailed information required to use the program described in Volume I of this report. This includes a description of the input data set, and the output results. A complete sample case is included in order to illustrate the use of the program. The full details of the method are described in Volume I, however, a brief description of the method is provided. The program is a numerical method that predicts the detailed pressure distribution on wing-body combinations at transonic Mach numbers less than one and integrates the pressures to obtain aircraft force and moment data. The code has been developed with the intent of providing the user with an easy to use and reliable tool. The basic inviscid prediction method is the modified transonic small disturbance theory program. In order to provide accurate surface pressure predictions on the wing, several additional features of the typical transonic flowfield 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.