NACA 0015 Kanat Profilinin Etrafındaki Akışın Firar Kenarından Akış Emme ile Kontrol Edilmesi
نویسندگان
چکیده
منابع مشابه
Ground Effect on the Aerodynamics of A NACA 0015 Airfoil with A Plain Trailing-Edge Flap
Submit Manuscript | http://medcraveonline.com Abbreviations: c: chord; u∞ : Free Stream Velocity; ν: Kinematic Viscosity; Re: Chord Reynolds number, ( ) / u c n ∞ = ; OGE: Out of the Ground Effect; GE: Ground Effect; Cd: Sectional Drag Coefficient; Cdp: Sectional Pressure Drag Coefficient; Cl: Sectional Lift Coefficient; Cl,max: Maximum Cl; l C α :Lift-Curve Slope; Cm: Sectional Pitching Moment...
متن کاملFlow Physics of Separated Flow over a Naca 0015 Airfoil and Detection of Flow Separation
J. P. Bonnet, W. L. Siauw, L. Cordier, J. Tensi Laboratoire d’Etudes Aérodynamiques, UMR CNRS 6609, ENSMA, Téléport 2, 1 Av. Clément Ader, BP 40109, 86961 Futuroscope Chasseneuil Cedex, France Bernd R. Noack Berlin Institute of Technology MB1 Straße des 17. Juni 135, D-10623 Berlin, Germany L. N. Cattafesta III Interdisciplinary Microsystems Group, University of Florida, Gainesville, FL, USA 32611
متن کاملGround Effect on the Aerodynamics of A NACA 0015 Airfoil with A Plain Trailing-Edge Flap
Submit Manuscript | http://medcraveonline.com Abbreviations: c: chord; u∞ : Free Stream Velocity; ν: Kinematic Viscosity; Re: Chord Reynolds number, ( ) / u c n ∞ = ; OGE: Out of the Ground Effect; GE: Ground Effect; Cd: Sectional Drag Coefficient; Cdp: Sectional Pressure Drag Coefficient; Cl: Sectional Lift Coefficient; Cl,max: Maximum Cl; l C α :Lift-Curve Slope; Cm: Sectional Pitching Moment...
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Özet. Yazılım projelerinde analiz aĢamasında tanımlanan probleme çözüm üretme aĢaması olan tasarım, geliĢtiriciler tarafından yazılımı gerçekleĢtirmek üzere yürütülen kodlama sürecine girdi sağlar. Yazılım geliĢtirilirken ya da güncellenirken, kod ve tasarımın uyumlu olarak idamesi uzun vadeli bir yatırımdır ve idame ettirilebilir bir proje sonucunu doğurur. Ancak gerçek hayatta tecrübesizlik, ...
متن کاملVerification of a CFD solver in near ground effect for aerodynamic behavior of airfoil NACA 0015
Numerical investigation was performed on NACA 0015 which is a symmetric airfoil. Pressure distribution and then lift and drag forces are verified. Changing of ground clearance was a considerable point. Also the angle of attack was changed from 0° to 10°. Pressure coefficient reaches its higher amounts on the wing lower surface when the ground clearance diminishes. Increment of the angle of atta...
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ژورنال
عنوان ژورنال: Bilecik Şeyh Edebali Üniversitesi Fen Bilimleri Dergisi
سال: 2019
ISSN: 2458-7575
DOI: 10.35193/bseufbd.588280