Transonic natural laminar flow nacelle optimization design at high Reynolds number

被引：0

作者：

Cao F. ^{[1
]}

Hu X. ^{[1
]}

Zhang M. ^{[1
]}

Tang Z. ^{[1
]}

机构：

[1] Key Laboratory of Unsteady Aerodynamics and Flow Control of Ministry of Industry and Information Technology, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing

来源：

Hangkong Dongli Xuebao/Journal of Aerospace Power | 2021年 / 36卷 / 08期

关键词：

Aerodynamic shape optimization; CST parameterization; Natural laminar flow nacelle; Transition prediction; Transition sensitivity analysis;

D O I：

10.13224/j.cnki.jasp.20200459

中图分类号：

学科分类号：

摘要：

To solve the problem of high⁃dimensional optimization design of laminar flow nacelle with large bypass ratio under high Reynolds number,three datum planes of nacelle were extracted to realize the optimal design of axisymmetric natural laminar flow.A wide range of laminar flow was obtained to reduce the surface friction resistance of the nacelle. An optimization system for the natural laminar flow (NLF) nacelle was established in combination with class and shape transformation (CST) parameterization,γ-Reθt transition model and the genetic algorithm.It showed the feasibility of establishing a three⁃dimensional NLF nacelle design method by optimizing the nacelle datum plane.Then,a three⁃dimensional non⁃axisymmetric NLF nacelle was constructed through the secondary development of CATIA,which solved the problem of efficiently importing a large number of data points and surface generation after the datum plane optimization. For the designed three⁃dimensional non⁃axisymmetric NLF nacelle,a transition sensitivity analysis of the angle of attack,sideslip angle,incoming Mach number,and turbulence intensity near the design point was conducted. The results showed that: under the condition of transonic speed,the laminar flow range decreased with the increase of the angle of attack;the laminar flow range increased with the increase of incoming Mach number;the sideslip angle and turbulence intensity had little effect on the laminar flow range. © 2021, Editorial Department of Journal of Aerospace Power. All right reserved.

引用

页码：1729 / 1739

页数：10

共 27 条

[11]

WANG Xun, CAI Jinsheng, QU Kun, Et al., Airfoil optimization based on improved CST parametric method and transition model, Acta Aeronautica et Astronautica Sinica, 36, 2, pp. 449-461, (2015)

[12]

LIAO Yanping, LIU Li, LONG Teng, The research on some parameterized methods for airfoil, Journal of Projectiles,Rockets,Missiles and Guidance, 31, 3, pp. 160-164, (2011)

[13]

KULFAN B M., Recent extensions and applications of the "CST" universal parametric geometry representation method[J], The Aeronautical Journal, 114, 1153, pp. 157-176, (2010)

[14]

KULFAN B M., Universal parametric geometry representation method[J], Journal of Aircraft, 45, 1, pp. 142-158, (2008)

[15]

SONG Wenping, WU Mengmeng, ZHU Zhen, Et al., Transition prediction methods towards significant drag reduction via laminar flow technology[J], Acta Aerodynamica Sinica, 36, 2, pp. 213-228, (2018)

[16]

SARIC W S., Physical description of boundary⁃layer transition:experimental evidence, (1994)

[17]

MENTER F R, LANGTRY R B, LIKKI S R, Et al., A correlation⁃based transition model using local variables:Part Ⅰ model formulation[J], Journal of Turbomachinery, 128, 3, pp. 413-422, (2006)

[18]

QIAO Lei, BAI Junqiang, HUA Jun, Et al., Improvement and verification of γ⁃Reθt¯ transition model, Journal of Aerospace Power, 30, 10, pp. 2488-2497, (2015)

[19]

HAN Zhonghua, WANG Shaonan, HAN Li, Et al., A novel method for automatic transition prediction of flows overairfoils based on dynamic mode decomposition, Acta Aeronautica et Astronautica Sinica, 38, 1, pp. 35-51, (2017)

[20]

LANGTRY R B, MENTER F R., Correlation⁃based transition modeling for unstructured parallelized computational fluid dynamics codes, AIAA Journal, 47, 12, pp. 2894-2906, (2009)

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