The paper describes the research aimed at reducing wall interference in wind tunnels 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 eliminates disadvantages of previously considered methods. The numerical study was conducted in the frame of electronic wind tunnel concept and ANSYS CFX software. The numerical investigation showed that the effect of shock wave reflection could be reduced using a new type of boundary condition that is a combination of perforated walls and a controlled boundary layer.


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    Title :

    Methods of the wall interference reduction at low supersonic velocities in wind tunnels


    Additional title:

    CEAS Aeronaut J


    Contributors:

    Published in:

    CEAS Aeronautical Journal ; 12 , 1 ; 205-211


    Publication date :

    2021-01-01


    Size :

    7 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






    Supersonic wind tunnels

    Keil, C.G. | Engineering Index Backfile | 1960


    Supersonic Wind Tunnels

    Keil, C.G. | Emerald Group Publishing | 1960


    Wall Interference in Two-Dimensional Wind Tunnels

    Kemp, William B., Jr. | NTRS | 1986