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

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