Design of supercritical natural laminar flow wing and its boundary layer transition wind tunnel test based on TSP technique

ZHANG Yanjun; DUAN Zhuoyi; LEI Wutao; BAI Junqiang; XU Jiakuan

doi:10.7527/S1000-6893.2018.22429

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2019 , Vol. 40 >Issue 4: 122429 - 122429

DOI: https://doi.org/10.7527/S1000-6893.2018.22429

Fluid Mechanics and Flight Mechanics

Design of supercritical natural laminar flow wing and its boundary layer transition wind tunnel test based on TSP technique

ZHANG Yanjun ,
DUAN Zhuoyi ,
LEI Wutao ,
BAI Junqiang ,
XU Jiakuan

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1. AVIC the First Aircraft Institute, Xi'an 710089, China;
2. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2018-06-07

Revised date: 2018-06-25

Online published: 2018-08-16

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Abstract

To achieve the green aviation goal of energy conservation and emission reduction, laminar flow design technology has become the hot research area for aircraft designers. For transonic airliners, supercritical natural laminar flow wing design technology will significantly reduce the flight drag, improve aerodynamic performance, and decrease fuel consumption and pollutant emissions. Based on the high-precision boundary layer transition prediction technique, the airfoil optimization design system is applied to design the supercritical natural laminar flow airfoils. Then the airfoils are arranged rationally to form the supercritical natural laminar flow wing. Numerical simulations of the supercritical natural laminar flow wing show satisfactory laminar flow characteristics. Then, a model with ratio of 1:10.4 is used to test the boundary layer transition in high speed and low turbulence wind tunnel in Netherland. The Temperature Sensitive Paint (TSP) technique is used to photograph laminar-turbulent area distribution at different Mach numbers, Reynolds numbers and angels of attack. At last, the boundary layer transition characteristics of the supercritical natural laminar flow wing are discussed, and the key factors of the wing design are summarized. In addition, the model can also be used to verify the accuracy of the boundary layer transition prediction technique for supercritical and high Reynolds numbers condition.

Key words： natural laminar flow; supercritical wing; high Reynolds number; boundary layer transition; Temperature Sensitive Paint (TSP); wind tunnel test

Cite this article

ZHANG Yanjun , DUAN Zhuoyi , LEI Wutao , BAI Junqiang , XU Jiakuan . Design of supercritical natural laminar flow wing and its boundary layer transition wind tunnel test based on TSP technique[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019 , 40(4) : 122429 -122429 . DOI: 10.7527/S1000-6893.2018.22429

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