The NASA Advanced Air Vehicles Program, Commercial Supersonics Technology Project seeks to advance tools and techniques to make over-land supersonic flight feasible. In this study, preliminary computational results are presented for future tests in the NASA Ames 9 foot x 7 foot supersonic wind tunnel to be conducted in early 2016. Shock-plume interactions and their effect on pressure signature are examined for six model geometries. Near- field pressure signatures are assessed using the CFD code USM3D to model the proposed test geometries in free-air. Additionally, results obtained using the commercial grid generation software Pointwise Reigistered Trademark are compared to results using VGRID, the NASA Langley Research Center in-house mesh generation program.


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    Title :

    Preliminary Computational Study for Future Tests in the NASA Ames 9 foot' x 7 foot Wind Tunnel



    Conference:

    AIAA Aerospace Sciences Meeting ; 2016 ; San Diego, CA, United States


    Publication date :

    2016-01-04


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :