{"title":"NACA 2312和NACA 2412气动性能的数值分析","authors":"Pritam Saha, Harshpreet Singh Kaberwal","doi":"10.38124/ijisrt20mar229","DOIUrl":null,"url":null,"abstract":"Comparison of the Aerodynamic Performance characteristics of NACA 2312 and NACA\n2412 aerofoils under the same flow conditions at a\nReynolds number of 2.74 x 106\nis presented. ANSYS is\nused for the creation of geometry and meshing and\nFLUENT is used as a solver. Coefficient of lift and\ncoefficient of drag for both aerofoils are compared for a\nrange of Angle of Attack while the free stream velocity\nof air is kept constant. This analysis can be used for the\nwing design and other aerodynamic modelling\ncorresponds to these aerofoils.","PeriodicalId":223657,"journal":{"name":"Volume 5 - 2020, Issue 3 - March","volume":"121 3 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2020-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Numerical Analysis of Aerodynamic Performance Characteristics of NACA 2312 and NACA 2412\",\"authors\":\"Pritam Saha, Harshpreet Singh Kaberwal\",\"doi\":\"10.38124/ijisrt20mar229\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"Comparison of the Aerodynamic Performance characteristics of NACA 2312 and NACA\\n2412 aerofoils under the same flow conditions at a\\nReynolds number of 2.74 x 106\\nis presented. ANSYS is\\nused for the creation of geometry and meshing and\\nFLUENT is used as a solver. Coefficient of lift and\\ncoefficient of drag for both aerofoils are compared for a\\nrange of Angle of Attack while the free stream velocity\\nof air is kept constant. This analysis can be used for the\\nwing design and other aerodynamic modelling\\ncorresponds to these aerofoils.\",\"PeriodicalId\":223657,\"journal\":{\"name\":\"Volume 5 - 2020, Issue 3 - March\",\"volume\":\"121 3 1\",\"pages\":\"0\"},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2020-03-31\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Volume 5 - 2020, Issue 3 - March\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.38124/ijisrt20mar229\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Volume 5 - 2020, Issue 3 - March","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.38124/ijisrt20mar229","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Numerical Analysis of Aerodynamic Performance Characteristics of NACA 2312 and NACA 2412
Comparison of the Aerodynamic Performance characteristics of NACA 2312 and NACA
2412 aerofoils under the same flow conditions at a
Reynolds number of 2.74 x 106
is presented. ANSYS is
used for the creation of geometry and meshing and
FLUENT is used as a solver. Coefficient of lift and
coefficient of drag for both aerofoils are compared for a
range of Angle of Attack while the free stream velocity
of air is kept constant. This analysis can be used for the
wing design and other aerodynamic modelling
corresponds to these aerofoils.
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