Experimental Aerodynamic Investigation of an UAV Wing with Wing Mounted Propellers
S Srinivasan1, Bhaskar K2, Supreeth R3
1Srinivasan S, Department of Aerospace Engineering, R V College of Engineering, Bangalore (Karnataka), India.
2Bhaskar K, Department of Aerospace Engineering, R V College of Engineering, Bangalore (Karnataka), India.
3Supreeth R, Department of Aerospace Engineering, R V College of Engineering, Bangalore (Karnataka), India.
Manuscript received on 23 May 2019 | Revised Manuscript received on 13 June 2019 | Manuscript Published on 27 June 2019 | PP: 288-295 | Volume-8 Issue-1C May 2019 | Retrieval Number: A10500581C19/2019©BEIESP
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: The present study aims at evaluating the aerodynamic coefficients of wing with and without propellers for various configurations at different locations. Also to ascertain the effect of clearance over the wing, wake survey analysis is performed for different clearances. It is observed that aerodynamic coefficients such as lift increased by 12 to 13% with a considerable reduction in drag of the order 2 to 3%, followed by increase in stall angle by 3° – 4°. The result is suitably bolstered by flow visualization technique, which indicated attached flow over the wing even at higher degrees of angle of attack. It is followed by an increase in dynamic pressure, being the obvious denouement to follow, therefore enhancing aerodynamic characteristics with an improved performance of UAVs.
Keywords: Propeller – Based Propulsion System, Aerodynamic Coefficients, Angle of Attack, UAV, Propeller Configuration, Coefficient of Lift, Coefficient of Drag, Stall.
Scope of the Article: Aerospace Engineering