非均匀来流下三维激波反问题的微元密切轴对称解法

周航; 金志光

doi:10.7527/S1000-6893.2020.24035

航空学报 >

2020 , Vol. 41 >Issue 12: 124035 - 124035

DOI: https://doi.org/10.7527/S1000-6893.2020.24035

流体力学与飞行力学

非均匀来流下三维激波反问题的微元密切轴对称解法

周航 ,
金志光

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南京航空航天大学能源与动力学院, 南京 210016

收稿日期: 2020-03-31

修回日期: 2020-07-23

网络出版日期: 2020-08-17

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Micro osculating axisymmetric flow method for 3D shock wave design under nonuniform flows

ZHOU Hang ,
JIN Zhiguang

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College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2020-03-31

Revised date: 2020-07-23

Online published: 2020-08-17

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摘要

传统的密切轴对称理论被广泛应用于均匀来流下的三维密切曲面激波反设计，为解决非均匀来流条件下的三维曲面激波反问题，提出了一种微元密切轴对称流场（MOA）求解方法。该方法沿激波面的周向和流向构建一系列微元密切面，在每个微元面内进行三维向二维流动的等效转换，从而突破了传统密切方法中不能有横向波后流动的限制。利用该方法编写设计程序，分别基于带攻角来流条件和外锥型流来流条件重构了标准内锥曲面激波，并与数值仿真结果进行了比较。结果表明，非均匀来流下激波曲面的三维形状均与预设形状完全一致，实现了非均匀来流下曲面激波形状可控。MOA方法在吸气式高超声速推进领域中前体/进气道一体化设计方面有重要应用前景。

关键词： 非均匀来流; 三维曲面激波; 微元密切轴对称方法; 乘波体; 高超声速进气道

本文引用格式

周航 , 金志光 . 非均匀来流下三维激波反问题的微元密切轴对称解法[J]. 航空学报, 2020 , 41(12) : 124035 -124035 . DOI: 10.7527/S1000-6893.2020.24035

Abstract

The traditional osculating axisymmetric flow theory is widely used in the inverse design of generalized shock waves under the condition of uniform incoming flows. To solve the inverse problem of the three-dimensional generalized shock wave design under nonuniform incoming flows, a novel method, Micro Osculating Axisymmetric flow (MOA) method, is proposed in this paper. The method constructs a series of micro osculating planes along the shock wave surface in both spanwise and streamwise directions. Actual three-dimensional flows are then approximated by two-dimensional axisymmetric flows in each micro osculating plane. Thus, the new method breaks the restriction of no lateral velocities or lateral pressure gradients in the traditional method. To validate its correctness and feasibility, an internal conical shock wave at a 4° angle of attack, and the other one in an external conical flow of a 10° cone half-angle are reconstructed by the novel method. The CFD results of the two cases indicate that the three-dimensional shock wave geometries completely match the prescribed ones, thereby realizing the control of the three-dimensional shock wave geometry under nonuniform incoming flows. The MOA method has significant application prospects in the field of air-breathing hypersonic forebody/inlet integrated design.

Key words： nonuniform incoming flows; three-dimensional curved shock waves; micro osculating axisymmetric flow method; waverider; hypersonic inlets

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