The fast maneuver of aerovehicles is one of the typical multiphysics coupled problems. The numerical virtual flight (NVF) simulation is a very useful and effective tool to analyze this kind of multiphysics problems. However, any computational-fluid-dynamics-based NVF solver should be verified and validated before engineering applications. In this work, the numerical virtual flight simulation platform Hybrid platform for engineering and research on FLOW - Numerical Virtual Flight System (HyperFLOW-NVFS), developed in our previous work (Zhang, L. P., Chang, X. H., Ma, R., Zhao, Z., and Wang, N. H., “A CFD-Based Numerical Virtual Flight Simulator and Its Application in Control Law Design of a Maneuverable Missile Model,” Chinese Journal of Aeronautics, Vol. 32, No. 12, 2019, pp. 2577–2591), is validated preliminarily by wind-tunnel virtual flight testing. A missile model is adopted to carry out virtual flight testing and numerical simulations. Three typical pitching-up maneuvering actions are tested to validate the capability of our NVF solver, including pitching up with a closed-loop attitude controller and an acceleration controller. The numerical results agree generally well with the experimental data, except for the states at a high angle of attack, which means that our NVF solver displays the potential for simulating complex multiphysics coupled problems.


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    Title :

    Validation of Numerical Virtual Flight System with Wind-Tunnel Virtual Flight Testing


    Contributors:
    Laiping, Zhang (author) / Zhongliang, Zhao (author) / Rong, Ma (author) / Xinghua, Chang (author) / Yuping, Li (author) / Nianhua, Wang (author) / Hao, Li (author)

    Published in:

    AIAA Journal ; 58 , 4 ; 1566-1579


    Publication date :

    2020-04-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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