Simulation and experiment of natural laminar flow flight test wing glove

WANG Hao; ZHONG Min; HUA Jun; ZHONG Hai; YANG Tihao; WANG Meng; LEI Guodong

doi:10.7527/S1000-6893.2022.26785

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2022 , Vol. 43 >Issue 11: 526785 - 526785

DOI: https://doi.org/10.7527/S1000-6893.2022.26785

Articles

Simulation and experiment of natural laminar flow flight test wing glove

WANG Hao ,
ZHONG Min ,
HUA Jun ,
ZHONG Hai ,
YANG Tihao ,
WANG Meng ,
LEI Guodong

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1. Department of Technology Ⅱ, Chinese Aeronautical Establishment, Beijing 100012, China;
2. AVIC Aeronautical Science and Technology Key Laboratory of Flight Simulation, CETE, Xi'an 710089, China;
3. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
4. Aero Science Key Lab of High Reynolds Aerodynamics Force of High Speed, AVIC Aerodynamics Research Institute, Shenyang 110034, China

Received date: 2021-12-08

Revised date: 2022-02-21

Online published: 2022-04-12

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Abstract

The development of green aviation has drawn increasing attention, while drag reduction by laminar flow region expansion is an important means to achieve energy conservation and emission reduction. This study simulates the wind tunnel and flight tests of a natural laminar flow wing glove by the numerical simulation method considering transition judgement. The pressure coefficient distribution of numerical simulation is consistent with that of the wind tunnel test, and the change in the transition location with angle of attack in numerical simulation is basically consistent with that in the wind tunnel test at atmospheric pressure. When the static pressure calculated from the flight height measured by the air data system, instead of that at the nose and the maximum cross section of the fuselage, is used as the reference pressure, the pressure coefficient distribution obtained from the flight test is more consistent with the simulation results. The transition positions of the wing glove obtained by numerical simulation in the design state and typical non-design state are in good agreement with that of the flight test. The momentum method is used to calculate the drag coefficient of the wing glove section, and the difference in drag coefficient reduction from the natural laminar flow between the numerical simulation and the flight test is smaller than 0.000 2.

Key words： natural laminar flow; wing glove; numerical simulation; wind tunnel test; flight test

Cite this article

WANG Hao , ZHONG Min , HUA Jun , ZHONG Hai , YANG Tihao , WANG Meng , LEI Guodong . Simulation and experiment of natural laminar flow flight test wing glove[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022 , 43(11) : 526785 -526785 . DOI: 10.7527/S1000-6893.2022.26785

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