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Aerodynamic Analysis of MAV's Wing Characteristics Affected by Propulsive Induced-Flow

Kwanchai Chinwicharnam, Chinnapat Thipyopas

Abstract


Multi-Mission Micro Aerial Vehicles (MAVs) are very small spy unmanned aircraft which able to complete the real and complex mission. Twin propeller system is applied in order to obtain zero torque and to perform hovering capability. Since propellers are installed at wing leading edge, strong effect of propulsive induced-flow occurs on the performance of wing, in particular for the MAVion. That has effect to flight condition. Therefore, this project aims to study the performance of MAVion’s wing which affected by the blowing flow from the propeller, specifically at speed of 5 10 and 15 m/s. Propulsive-induced flow is integrated in the analytical study. Input-thrust is estimated by equilibrium in forces (lift&drag) for level flight condition. The aerodynamic performance of wing is analyzed by Computational Fluid Dynamic tool using ANSYS. Disc actuator theory is applied to simulate the propeller in the simulation. Due to performance of PC, 2,000,000 elements are used, however fine elements at wing surface are carefully selected. The CFD result of the original MH45 wing is validated by wind tunnel test result from ISAE. The propulsive induced-flow can extend the delay of stall and separation on the wing providing very high angle of attack up to vertical flight. Finally, lift, drag, and lift-to-drag ratio between wing with and without effect from propeller are analyzed and compared.


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References


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DOI: http://dx.doi.org/10.21535%2FProICIUS.2012.v8.779

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