S.L. Chernyshev , A.I. Ivanov , E.V.Streltsov , A.O. Volkova

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_43001166

The paper describes the research aimed at reducing the wall interference in the wind tunnel at low supersonic velocities. The results of such wind tunnel tests are often affected by wave perturbations generated by the model and reflected from the test section walls. This research describes the methods that can effectively reduce the wave reflection from the wall. A numerical investigation is presented that includes a novel boundary condition that allows eliminating disadvantages of previously considered methods. The numerical study was conducted in the frame of Electronic Wind Tunnel (EWT TsAGI) concept and ANSYS CFX software. The numerical investigation showed that the effect of shock wave reflection could be reduced by using a new type of boundary condition that is a combination of perforated walls and a controlled boundary layer.

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In Categories: HiSST 2018, Hypersonic Aerodynamics, Testing and Evaluation
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