马赫数为 2 时弱冲击波对掠过平板上边界层流动作用的实验研究

IF 0.5 4区工程技术 Q4 ENGINEERING, AEROSPACE

Thermophysics and Aeromechanics Pub Date : 2024-12-13 DOI:10.1134/S0869864324030077

A. D. Kosinov, N. V. Semionov, A. V. Shmakova, A. A. Yatskikh

{"title":"马赫数为 2 时弱冲击波对掠过平板上边界层流动作用的实验研究","authors":"A. D. Kosinov, N. V. Semionov, A. V. Shmakova, A. A. Yatskikh","doi":"10.1134/S0869864324030077","DOIUrl":null,"url":null,"abstract":"<div><p>The action of a pair of weak shock waves on a supersonic boundary layer on a swept flat plate with a bluntness radius of the leading edge equal to 2.5 mm at the Mach number 2 is experimentally studied. Transverse hot-wire measurements are performed in the boundary layer with a fixed distance of the probe from the model surface. It is found that a change in the sweep angle of the leading edge from 35 to 45 degrees reduces the intensity of the action of the weak shock waves on the boundary layer flow. As the sweep angle of the leading edge increases to 50°, the weak shock waves no longer affect the flow in the supersonic boundary layer on the swept plate.</p></div>","PeriodicalId":800,"journal":{"name":"Thermophysics and Aeromechanics","volume":"31 3","pages":"459 - 464"},"PeriodicalIF":0.5000,"publicationDate":"2024-12-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Experimental study of the action of weak shock waves on the boundary layer flow on a swept flat plate at the Mach number 2\",\"authors\":\"A. D. Kosinov, N. V. Semionov, A. V. Shmakova, A. A. Yatskikh\",\"doi\":\"10.1134/S0869864324030077\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"<div><p>The action of a pair of weak shock waves on a supersonic boundary layer on a swept flat plate with a bluntness radius of the leading edge equal to 2.5 mm at the Mach number 2 is experimentally studied. Transverse hot-wire measurements are performed in the boundary layer with a fixed distance of the probe from the model surface. It is found that a change in the sweep angle of the leading edge from 35 to 45 degrees reduces the intensity of the action of the weak shock waves on the boundary layer flow. As the sweep angle of the leading edge increases to 50°, the weak shock waves no longer affect the flow in the supersonic boundary layer on the swept plate.</p></div>\",\"PeriodicalId\":800,\"journal\":{\"name\":\"Thermophysics and Aeromechanics\",\"volume\":\"31 3\",\"pages\":\"459 - 464\"},\"PeriodicalIF\":0.5000,\"publicationDate\":\"2024-12-13\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Thermophysics and Aeromechanics\",\"FirstCategoryId\":\"5\",\"ListUrlMain\":\"https://link.springer.com/article/10.1134/S0869864324030077\",\"RegionNum\":4,\"RegionCategory\":\"工程技术\",\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"Q4\",\"JCRName\":\"ENGINEERING, AEROSPACE\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Thermophysics and Aeromechanics","FirstCategoryId":"5","ListUrlMain":"https://link.springer.com/article/10.1134/S0869864324030077","RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q4","JCRName":"ENGINEERING, AEROSPACE","Score":null,"Total":0}

引用次数: 0

摘要

实验研究了在马赫数为 2 时，一对弱冲击波对前缘钝角半径等于 2.5 毫米的扫过平板上的超音速边界层的作用。在边界层中进行了横向热线测量，探头与模型表面的距离固定。结果发现，前缘扫掠角从 35 度到 45 度的变化降低了弱冲击波对边界层流动的作用强度。当前缘扫掠角增加到 50 度时，弱冲击波不再影响扫掠板上超音速边界层的流动。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

查看原文本刊更多论文

Experimental study of the action of weak shock waves on the boundary layer flow on a swept flat plate at the Mach number 2

The action of a pair of weak shock waves on a supersonic boundary layer on a swept flat plate with a bluntness radius of the leading edge equal to 2.5 mm at the Mach number 2 is experimentally studied. Transverse hot-wire measurements are performed in the boundary layer with a fixed distance of the probe from the model surface. It is found that a change in the sweep angle of the leading edge from 35 to 45 degrees reduces the intensity of the action of the weak shock waves on the boundary layer flow. As the sweep angle of the leading edge increases to 50°, the weak shock waves no longer affect the flow in the supersonic boundary layer on the swept plate.

求助全文

通过发布文献求助，成功后即可免费获取论文全文。去求助

来源期刊

Thermophysics and Aeromechanics THERMODYNAMICS-MECHANICS

CiteScore

0.90

自引率

40.00%

发文量

审稿时长

>12 weeks

期刊介绍： The journal Thermophysics and Aeromechanics publishes original reports, reviews, and discussions on the following topics: hydrogasdynamics, heat and mass transfer, turbulence, means and methods of aero- and thermophysical experiment, physics of low-temperature plasma, and physical and technical problems of energetics. These topics are the prior fields of investigation at the Institute of Thermophysics and the Institute of Theoretical and Applied Mechanics of the Siberian Branch of the Russian Academy of Sciences (SB RAS), which are the founders of the journal along with SB RAS. This publication promotes an exchange of information between the researchers of Russia and the international scientific community.