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Abstract:
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This paper describes an investigation of
aerodynamic performance and a Mild-Stall characteristic
of the designed airfoil for Fixed-Wing Unmanned Aerial
Vehicle (Fixed-Wing UAV). The numerical simulations of
Lift force and Drag force of the designed airfoil from
numerical results by using Computational Fluid Dynamics
(CFD) are compared with an experiment. The
computational domain was discretized using an
unstructured mesh of 7,100,000 elements. The steady and
incompressible flow with a Realizable K-epsilon
turbulence model is used in all study cases. The
simulations were held at a Reynolds number of 1,000,000.
Results show the force coefficients and also the velocity
contours and streamlines at different angle of attack, from
0 to 20 degrees. The results support that this designed
airfoil can achieve the Mild-Stall characteristic. Lift force
is decreased slightly in the mild-stall region after the angle
of attack generated the maximum Lift force. This can
extend the range of flight lift coefficient and help to
provide a safe flight in gusty wind. |