A. Yadav, Dhruv P. Suthar, Hetal Bhatiya, Aniruddh Marakana, Mohammad Shadab Ghanchi, Sathish Dharmalingam
{"title":"Experimental Investigations on Aerodynamic Performances of NACA0012 Airfoil","authors":"A. Yadav, Dhruv P. Suthar, Hetal Bhatiya, Aniruddh Marakana, Mohammad Shadab Ghanchi, Sathish Dharmalingam","doi":"10.1109/ICICCSP53532.2022.9862440","DOIUrl":null,"url":null,"abstract":"The aerodynamic characteristics for the various angles of attack at different Reynolds numbers with a view to extending the knowledge of the pressure distribution over the NACA 0012 airfoil have been measured in a low-speed subsonic wind tunnel. Experiments were carried out by varying the angle of attack from −30 to +30 degrees and the velocity varied from 10 m/s to 25 m/s. The lift coefficient and drag coefficient for the NACA 0012 airfoil are obtained by measuring the pressure distribution from the pressure ports situated over the airfoil surface.","PeriodicalId":326163,"journal":{"name":"2022 International Conference on Intelligent Controller and Computing for Smart Power (ICICCSP)","volume":null,"pages":null},"PeriodicalIF":0.0000,"publicationDate":"2022-07-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"2022 International Conference on Intelligent Controller and Computing for Smart Power (ICICCSP)","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1109/ICICCSP53532.2022.9862440","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
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Abstract
The aerodynamic characteristics for the various angles of attack at different Reynolds numbers with a view to extending the knowledge of the pressure distribution over the NACA 0012 airfoil have been measured in a low-speed subsonic wind tunnel. Experiments were carried out by varying the angle of attack from −30 to +30 degrees and the velocity varied from 10 m/s to 25 m/s. The lift coefficient and drag coefficient for the NACA 0012 airfoil are obtained by measuring the pressure distribution from the pressure ports situated over the airfoil surface.
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