An experience of using CFD methods in experimental works in TsAGI

A description of method for calculating the flow around aircraft model in wind tunnel is presented. Special boundary conditions, which permit to achieve necessary flow parameters in control section and to simulate some peculiarities of wind tunnel walls, for example, perforation, are formulated. Problems of numerical solution convergence acceleration are considered, in particular, a method of implicit smoothing that permits to diminish the calculation time for some ones is shown. Examples of practical using the proposed methodology are presented. It is shown that in conditions of subsonic TsAGI wind tunnel, one can simulate influence of construction elements, which are absent in this wind tunnel (for example, running way), on the model. A mathematical model of European wind tunnel (EWT) with slotted walls is presented. It is shown that flow in mixing zone influences in the main flow in test section of this wind tunnel. Data about influence of model sting in TsAGI wind tunnel T-128 are presented. Height of pedestal that is used in “half-model” tests in this wind tunnel is justified. A conclusion that mathematical model of wind tunnel is an obligatory part of experimental investigation method is made.