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Experimental investigation of angle of attack effects on
aerodynamics characteristics of
delta wing-body-vertical tail combination airplane model in ground
effects
Aerospace Engineering, Aerospace Institute, Tehran, Iran A. Ghajar
Aerospace Engineering, Aerospace Institute, Tehran, Iran S. A.
Seyed Shams Taleghani Department of Aerospace Engineering,
University of Sharif, Tehran, Iran M. R. Soltani Faculty of New
Sciences and Technologies, University of Tehran, Tehran, Iran M.
Masdari
Abstract Aerodynamic characteristics of an aircraft with delta wing
are considerably affected under the ground effect in take-off and
landing phases. In this research, static ground effect of a 60
degrees delta wing with axisymmetric sharp edges in combination of
body and vertical tail at low speed wind tunnel are investigated.
The wind tunnel is closed type has an opened test section that its
dimensions is 2.8 m × 2.2 m and maximum velocity is 90 m/s. In
these tests ground effect is simulated using a fixed plane that its
height is variable. With decreasing the height from the ground
plane, the lift force is increased, induced drag force is
decreased, total drag force is increased and nose-down pitching
moment is increased nonlinearly. The rate of increasing of lift
coefficient in linear regions increased with decreasing of height
from ground plane. At the positive angle of attack the most
percentage increasing of lift coefficient is due to 5 degrees angle
of attack as the result of existence of perfect vortex flow over
the whole wing surface. The minimum case is due to 30 degrees of
angle of attack. Keywords: Wind tunnel, Ground Simulator, Delta
Wing, Aerodynamics Coefficients.
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