Numerical Method For Unsteady Transonic Flow About Wings With Control Surfaces

摘要

This article introduces a type of finite difference calculation method forunsteady transonic speed flows associated with wings having control surfaces. The equations which are chosen for use are modified three dimensional nonsteady transonic speed small perturbation geopotential equations. Use is made of time integration methods. Solution forms are approximate factor type resolutions of alternating direction implicit (ADI) type forms. Use is made of this type of method to calculate the unsteady aerodynamic forces associated with F-5 wings in oncoming flows with Mach numbers or 0.9 and 0.925 as well as the unsteady aerodynamic forces associated with control surface oscillations. Comparisons were carried out of calculation results with NLR test results from outside of China and calculation results from XTRAN3S methods. This clearly showed that calculations were successful.