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Journal of Aerospace Science and Technology، جلد ۱۴، شماره ۱، صفحات ۱۰۳-۱۱۰
عنوان فارسی Experimental Investigation of using Plasma Actuators as Virtual Gurney Flap
چکیده فارسی مقاله The primary objective of this study was to demonstrate how plasma actuators could be used to discharge a perpendicular dielectric barrier as a virtual Gurney flap. This study utilized wind tunnel experiments on a flat plate airfoil. Each experiment is conducted at two different free flow velocities of ten and twenty meters per second. To study and extract the aerodynamic phenomena generated by plasma actuators and to compare them to the Gurney phenomena of a physical flap, velocity profiles in the model sequence were measured using a hot wire flow meter in two different longitudinal positions relative to the model. All experiments were conducted from five distinct vantage points, 0, 2, 4, 6, and 8, and plasma actuators were activated in two distinct settings to extract concepts under a variety of conditions. Wind tunnel experiments indicate that downward sequence transfer occurs when plasma actuators are used. Additionally, there are two distinct types of vortex shedding on the model's back: one that resembles Karman vortex shedding and another that occurs below the model. The observation of velocity profiles demonstrates that the deformation of the sequence caused by the use of plasma actuators is very similar to that caused by an airfoil sequence equipped with a physical Gurney flap.
کلیدواژه‌های فارسی مقاله
عنوان انگلیسی Experimental Investigation of using Plasma Actuators as Virtual Gurney Flap
چکیده انگلیسی مقاله The primary objective of this study was to demonstrate how plasma actuators could be used to discharge a perpendicular dielectric barrier as a virtual Gurney flap. This study utilized wind tunnel experiments on a flat plate airfoil. Each experiment is conducted at two different free flow velocities of ten and twenty meters per second. To study and extract the aerodynamic phenomena generated by plasma actuators and to compare them to the Gurney phenomena of a physical flap, velocity profiles in the model sequence were measured using a hot wire flow meter in two different longitudinal positions relative to the model. All experiments were conducted from five distinct vantage points, 0, 2, 4, 6, and 8, and plasma actuators were activated in two distinct settings to extract concepts under a variety of conditions. Wind tunnel experiments indicate that downward sequence transfer occurs when plasma actuators are used. Additionally, there are two distinct types of vortex shedding on the model's back: one that resembles Karman vortex shedding and another that occurs below the model. The observation of velocity profiles demonstrates that the deformation of the sequence caused by the use of plasma actuators is very similar to that caused by an airfoil sequence equipped with a physical Gurney flap.
کلیدواژه‌های انگلیسی مقاله Flow control,plasma actuators,Wind tunnel,virtual Gurney flap,hot wire flow meter
نویسندگان مقاله Bahareh Mojarrad |
DANA Aerodynamic Laboratory, Amirkabir University of Technology

Saeed Oveisi |
Faculty of Aerospace Engineering, Amirkabir University of Technology

Mostafa Kazemi |
Faculty of Aerospace Engineering, Amirkabir University of Technology

Mahmoud Mani |
Faculty of Aerospace Engineering, Amirkabir University of Technology

نشانی اینترنتی https://jast.ias.ir/article_139875_c22d8f4773fb45025fcbda874f8fe447.pdf
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