Volume 2, Issue 1 (2-2017)                   jste 2017, 2(1): 42-48 | Back to browse issues page

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Investigation of the effects of boundary layer heating on the aerodynamics coefficients of transonic airfoil using the computational fluid dynamics. jste. 2017; 2 (1) :42-48
URL: http://yujs.yu.ac.ir/jste/article-1-46-en.html
Abstract:   (3441 Views)

This study aims at investigating aerodynamic coefficients changes by applying a two-dimensional heat flux on the wing in transonic regime. The numerical and experimental researches have shown that heat transfer on the fuselage has a significant impact on reducing drag (force). The current study aims also at investigating the effects of the heat transfer on aerodynamic coefficients of wing section. Accordingly, the turbulent transonic flow was numerically simulated around RAE2822 transonic airfoil with two different methods of modeling turbulent flow, namely, k–ε two-equation method and Reynolds stress five-equation model (RSM) and the obtained results were compared with experimental results. After choosing RSM as an appropriate method, subsequent investigations have been carried out with it. By applying heat flux in certain parts of upper and lower airfoil, the flow around it, is modeled and aerodynamic coefficients are extracted for airfoil and investigated. Studies showed that heating below the airfoil surface leads to change of aerodynamic coefficients with increasing the lift to drag ratio which can reduce fuel consumption and increase endurance of aircraft.

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Type of Study: Research | Subject: Special
Received: 2016/03/13 | Accepted: 2016/07/27 | Published: 2017/01/30

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