This paper presents a combined experimental and computational study of a low-sweep transonic natural laminar flow (NLF) wing with shock-control bumps (SCBs). A transonic NLF wing with a relatively low sweep angle of 20 deg was chosen for this study. To avoid the complexity of the flow introduced by perforated/slotted walls commonly used for transonic wind-tunnel tests for reducing the wall interference, both experimental tests and computational simulations were conducted with solid wind-tunnel wall conditions. This allows for like-to-like validation of the computational simulation. Optimization of the shock-control bumps was first conducted to design the wind-tunnel test model with bumps. Two critical parameters of the three-dimensional SCBs for shock control (i.e., bump crest position and bump height) were optimized in terms of total drag reduction at the given design point in the wind tunnel. We show that the strong shock wave on the low-sweep NLF wing can be effective controlled by well-designed SCBs deployed along the wing span. The optimized SCBs result in 18.5% pressure drag reduction with 5% viscous drag penalty, and the SCBs also bring some benefits at off-design conditions. The wind-tunnel tests include pressure measurement, particle image velocimetry, and temperature-sensitive paint to provide detailed insight into the shock-control flowfield and to validate the computational simulations. Comparisons include surface pressure profile, velocity distribution, and transition location.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Shock Control of a Low-Sweep Transonic Laminar Flow Wing


    Contributors:
    Zhu, Maolin (author) / Li, Yonghong (author) / Qin, Ning (author) / Huang, Yong (author) / Deng, Feng (author) / Wang, Yibin (author) / Zhao, Ning (author)

    Published in:

    AIAA Journal ; 57 , 6 ; 2408-2420


    Publication date :

    2019-02-13


    Size :

    13 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Benefit Assessment of Low-Sweep Transonic Natural Laminar Flow Wing for Commercial Aircraft

    Fan, Zhouwei / Yu, Xiongqing / Qin, Ning et al. | AIAA | 2021



    The effect of wing sweep on laminar flow

    Gray, W. E. | TIBKAT | 1952


    An Analysis of Transonic Flow Around Double Sweep Back Wing

    Rho, O. / Kim, J. H. | British Library Conference Proceedings | 1993


    Aerostructural Optimization of a Low Sweep Transonic Wing with Shock Control Bump (AIAA 2016-0160)

    Elham, Ali / Timmer, Bram | British Library Conference Proceedings | 2016