Automatic transition prediction for natural-laminar-flow wing design of supersonic transports

NIE Han; SONG Wenping; HAN Zhonghua; CHEN Jianqiang; DUAN Maochang; WAN Bingbing

doi:10.7527/S1000-6893.2021.26342

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2022 , Vol. 43 >Issue 11: 526342 - 526342

DOI: https://doi.org/10.7527/S1000-6893.2021.26342

Articles

Automatic transition prediction for natural-laminar-flow wing design of supersonic transports

NIE Han ,
SONG Wenping ,
HAN Zhonghua ,
CHEN Jianqiang ,
DUAN Maochang ,
WAN Bingbing

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1. Research Center for Environment-Friendly Supersonic Civil Transports (ReCESST)/Institute of Aerodynamic and Multidisciplinary Design Optimization, School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, Northwestern Polytechnical University, Xi'an 710072, China;
3. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received date: 2021-09-09

Revised date: 2021-09-26

Online published: 2021-12-01

Supported by

National Natural Science Foundation of China (12072285, 11972305); Shaanxi Science Fund for Distinguished Young Scholars (2020JC-13); National Numerical Windtunnel Project (2018-ZT1A03)

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Abstract

Automatic transition prediction is crucial for the natural-laminar-flow wing design of supersonic transports. Traditional transition prediction methods for low speed and transonic laminar-flow wing design generally only consider 2D Tollmien-Schlichting (TS) waves and stationary Crossflow (CF) waves, which are not suitable for prediction of flow transition induced by oblique TS or traveling CF waves in supersonic boundary layers. This study develops an e^N transition prediction method with an improved amplification factor computation strategy, taking into account three-dimensional oblique TS waves and traveling CF waves. This method adopts the fixed-wave-angle and fixed-frequency methods to search for unstable TS and CF modes and the fixed-transverse-wavenumber-and-fixed-frequency method or the envelope method to compute amplification factors of perturbations. The method is further coupled with a Reynolds-Averaged Navier-Stokes equation (RANS) solver for automatic transition prediction in flow simulation. The proposed method is used to analyze boundary-layer stability of NASA's experiment 65°-swept-wing at Mach number 2.0. The computed amplification factors of traveling and stationary CF waves agree well with the results in the reference work. Furthermore, the proposed method is applied to natural-laminar-flow design of an infinite-span swept wing with a swept angle of 60° at Mach number 2.0, Reynolds number 1.39×10⁷. We propose an ideal pressure distribution which quickly accelerates the flow near the leading edge and then keeps it in a mild pressure gradient. The designed wing is evaluated and nearly full laminar flow is observed over the upper surface, indicating the applicability of our method for aerodynamic design of the natural-laminar-flow wing of supersonic transports.

Key words： supersonic transports; natural laminar flow; linear stability theory; e^N method; transition prediction

Cite this article

NIE Han , SONG Wenping , HAN Zhonghua , CHEN Jianqiang , DUAN Maochang , WAN Bingbing . Automatic transition prediction for natural-laminar-flow wing design of supersonic transports[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022 , 43(11) : 526342 -526342 . DOI: 10.7527/S1000-6893.2021.26342

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