The Pressure on Flat and Anhedral Delta Wings with Attached Shock Waves

Author:

Pike J

Abstract

SummaryAn expression is derived which relates the pressure on a wing in a supersonic free stream to the pressure on a thin wing with the same surface shape. The expression is used to find the pressure distribution for caret wings and flat delta wings with attached flow at their leading edges. The compression surface pressure distributions found are in good agreement with existing experimental and theoretical results, except when large pressure changes occur in the flow behind the attached shock wave. Some expansion surface results are also obtained for wings with an isentropic expansion at the leading edge. The effects of flow and geometry changes on the pressure distribution are investigated. It is found that a small improvement in the lift/drag ratio of a caret wing can be obtained by halving the anhedral required for the plane shock wave condition.

Publisher

Cambridge University Press (CUP)

Subject

General Engineering

Reference14 articles.

1. Voskresenskii G P Numerical solution of the problem of a supersonic gas flow past an arbitrary surface of a delta wing in the compression region. Izv Akad Nauk SSSR, Mekh Zhid 1, Gaya 4, 1968.

2. Squire L C Pressure distributions and flow patterns at M = 4.0 on some delta wings. ARC R&M 3373, 1964.

3. Pike J The flow past flat and anhedral delta wings with attached shock waves. RAE Technical Report 71081, April 1971.

4. Roe P L A special off-design flow for caret wings. Private communication.

5. NUMERICAL SOLUTION OF THE PROBLEM OF SUPERSONIC FLOW PAST THE LOWER SURFACE OF A DELTA WING

Cited by 6 articles. 订阅此论文施引文献 订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献

1. Computational and Analytical Investigation of Aerodynamic Derivatives of Similitude Delta Wing Model at Hypersonic Speeds;International Journal of Technology;2017-04-29

2. A demonstrator for the SSTO launcher with combined cycle propulsion;Philosophical Transactions of the Royal Society of London. Series A: Mathematical, Physical and Engineering Sciences;1999-08

3. Structure of the Conical Flowfield about External Axial Corners;AIAA Journal;1979-01

4. Experimental investigation of some singularities of the supersonic flow around V-shaped wings;Fluid Dynamics;1976

5. Some Extensions of Thin-Shock-Layer Theory;Aeronautical Quarterly;1974-02

同舟云学术

1.学者识别学者识别

2.学术分析学术分析

3.人才评估人才评估

"同舟云学术"是以全球学者为主线,采集、加工和组织学术论文而形成的新型学术文献查询和分析系统,可以对全球学者进行文献检索和人才价值评估。用户可以通过关注某些学科领域的顶尖人物而持续追踪该领域的学科进展和研究前沿。经过近期的数据扩容,当前同舟云学术共收录了国内外主流学术期刊6万余种,收集的期刊论文及会议论文总量共计约1.5亿篇,并以每天添加12000余篇中外论文的速度递增。我们也可以为用户提供个性化、定制化的学者数据。欢迎来电咨询!咨询电话:010-8811{复制后删除}0370

www.globalauthorid.com

TOP

Copyright © 2019-2024 北京同舟云网络信息技术有限公司
京公网安备11010802033243号  京ICP备18003416号-3