Full Article: PDF
Scientific Object Identifier: http://s-o-i.org/1.1/TAS-09-101-73
DOI: https://dx.doi.org/10.15863/TAS.2021.09.101.73
Language: English
Citation: Chemezov, D., et al. (2021). Pressure distribution on the surfaces of the NACA 0012 airfoil under conditions of changing the angle of attack. ISJ Theoretical & Applied Science, 09 (101), 601-606. Soi: http://s-o-i.org/1.1/TAS-09-101-73 Doi: https://dx.doi.org/10.15863/TAS.2021.09.101.73 |
Pages: 601-606
Published: 30.09.2021
Abstract: The results of computer calculation of changing pressure of air flows on the surfaces of the NACA 0012 airfoil under conditions of subsonic flight speed of the aircraft are presented in the article. The formation of zones of positive and negative pressure near the upper and lower surfaces of the wing (lift), which provide takeoff or landing of the aircraft, occurs when changing the angle of attack of the airfoil in the range from 15 to -15 degrees. The maximum pressure values were determined at the leading and trailing edges of the airfoil. The calculated pressure values will be valid when air flows around the symmetrical airfoil.
Key words: the airfoil, the angle of attack, pressure, subsonic flight speed.
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