新型人工转捩技术及风洞试验验证

doi:10.7527/S1000-6893.2014.0284

流体力学与飞行力学

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新型人工转捩技术及风洞试验验证

赵子杰, 高超, 张正科

西北工业大学航空学院, 西安 710072

收稿日期:2014-08-18 修回日期:2014-09-09 出版日期:2015-06-15 发布日期:2014-10-31
通讯作者: 张正科 Tel.: 029-88491224-15 E-mail: zkzhang@nwpu.edu.cn E-mail:zkzhang@nwpu.edu.cn
作者简介:赵子杰男, 博士研究生。主要研究方向: 跨声速空气动力学, 流动控制。 E-mail: zhaozijie84@gmail.com;高超男, 博士, 教授, 博士生导师。主要研究方向: 实验空气动力学, 计算空气动力学。 Tel: 029-88491224-12 E-mail: gaochao@nwpu.edu.cn;张正科男, 博士, 教授, 硕士生导师。主要研究方向: 计算空气动力学。 Tel: 029-88491224-15 E-mail: zkzhang@nwpu.edu.cn
基金资助:
西北工业大学基础研究基金 (JC-201103); 航空科学基金 (2013ZD53057)

An innovative artificial transition technique and its validation through wind tunnel tests

ZHAO Zijie, GAO Chao, ZHANG Zhengke

School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received:2014-08-18 Revised:2014-09-09 Online:2015-06-15 Published:2014-10-31
Supported by:
NPU Basic Research Foundation (JC-201103); Aeronautical Science Foundation of China (2013ZD53057)

摘要/Abstract

摘要：

给出了一种新型分布型人工转捩粗糙元设计技术,该技术解决了传统人工转捩方法在跨声速风洞试验中存在的效率低、可靠性和重复性差等问题。通过理论研究确定了该转捩技术的形式,包括粗糙元形状、高度和排列方式等技术参数以及针对不同模型的设计方案;同时对翼型模型(NACA0012)和全机模型(GBM-01或AGARD-B标模)在不同马赫数和迎角下分别进行了测压和测力风洞试验,借助升华法,对人工转捩技术的边界层转捩效果进行了验证研究。结果表明:在不同模型上使用不同的设计方案,该转捩技术可以得到可靠的固定转捩效果,并获得具有大气飞行中高雷诺数特点的气动力结果。

关键词: 跨声速空气动力学, 跨声速风洞, 人工转捩, 粗糙元, 升华法, 边界层

Abstract:

An innovative artificial transition technique of distributed roughness elements is designed aimed at solving the problems encountered in fixed artificial transition tests with traditional methods in transonic wind tunnel. The shape, height and arrangement of the roughness elements and the design schemes for different configurations of models are determined by theoretical analysis. Meanwhile, the pressure coefficient on an airfoil surface (NACA0012) and the aerodynamic coefficients on an airplane model (GMB-01, or AGARD-B calibration model) are measured in the tests of artificial fixed transition. Sublimation flow visualization technique is used to judge or identify transition. The differences between natural free transition and artificial fixed transition are analyzed. The effectiveness of the innovative artificial transition technique is observed and analyzed. The results show that this kind of innovative artificial transition technique can trigger boundary layer transition from laminar to turbulent and is able to obtain aerodynamic results comparable to those at the high Reynolds number atmospheric flight conditions.

Key words: transonic aerodynamics, transonic wind tunnel, artificial transition, roughness elements, sublimation method, boundary layer

中图分类号:

V211.7

赵子杰, 高超, 张正科. 新型人工转捩技术及风洞试验验证[J]. 航空学报, 2015, 36(6): 1830-1838.

ZHAO Zijie, GAO Chao, ZHANG Zhengke. An innovative artificial transition technique and its validation through wind tunnel tests[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 1830-1838.

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E-mail：hkxb@buaa.edu.cn

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新型人工转捩技术及风洞试验验证

An innovative artificial transition technique and its validation through wind tunnel tests

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