{"title":"Determination of the effect due wall interference on the flow around airfoil in the T-128 wind tunnel","authors":"S. A. Glazkov, A. V. Semenov","doi":"10.1134/S086986432303006X","DOIUrl":null,"url":null,"abstract":"<div><p>Within the framework of linear subsonic theory, the problem of determining the effect due to wall interference on the flow around airfoil according to the pressure distributions measured on the airfoil and on the wind-tunnel test section walls is solved. For the test case (testing a BGK1 airfoil in the IAR1.5m wind tunnel), we compared the wall interference corrections to freestream Mach number and airfoil angle-of-attack that were obtained using our method and in the works by other authors. For an OSPB-77 airfoil model tested in the T-128 wind tunnel for two values of wall permeability, <i>f</i> = 0 and 3 %, corrections to distributed data and integral loads were applied in the range of Mach numbers from 0.2 to 0.78. The application of those corrections has made it possible to bring the results for <i>f</i> = 0 and <i>f</i> = 3 % in closer agreement up to the angles of attack at which flow separation occurs on the airfoil.</p></div>","PeriodicalId":800,"journal":{"name":"Thermophysics and Aeromechanics","volume":null,"pages":null},"PeriodicalIF":0.5000,"publicationDate":"2023-10-23","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/S086986432303006X","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
Abstract
Within the framework of linear subsonic theory, the problem of determining the effect due to wall interference on the flow around airfoil according to the pressure distributions measured on the airfoil and on the wind-tunnel test section walls is solved. For the test case (testing a BGK1 airfoil in the IAR1.5m wind tunnel), we compared the wall interference corrections to freestream Mach number and airfoil angle-of-attack that were obtained using our method and in the works by other authors. For an OSPB-77 airfoil model tested in the T-128 wind tunnel for two values of wall permeability, f = 0 and 3 %, corrections to distributed data and integral loads were applied in the range of Mach numbers from 0.2 to 0.78. The application of those corrections has made it possible to bring the results for f = 0 and f = 3 % in closer agreement up to the angles of attack at which flow separation occurs on the airfoil.
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.
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