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In this research experimental results of 60 degree delta wing airplane that conducted in National Low Speed Wind Tunnel is presented. The wind tunnel is closed type has an opened test section that its dimensions are 2.8 m × 2.2 m. Tests Reynolds number is beyond 1.5 million that achievement of this Reynolds number at low speed is unique in the country. Ground effect is measured using a fixed plane that its height is variable. Tests are conducted at the different height and aerodynamics forces and moments are measured using a sting type six component strain gaged balance. The tests results showed that the maximum lift coefficients increased from 1.29 to 1.38 due to presence of the ground plane. The lift coefficient due to ground plane in all range of angle of attack is increased and induced drag coefficient is decreased and consequently, the overall aerodynamics efficiency (lift to drag ratio) is increased from 8 to 14.5. When the distance between model and ground plane is less than half of the wing span, lift curve slope is increased in high rate from 2.66 per radian to 3.11 per radian. Decreasing this distance is caused the aerodynamic center is shifted backward and consequently longitudinal static stability is increased. Consequently presence of ground plane is caused increasing of airplane static stability.

Keywords: Wind tunnel, Ground Simulator, Delta wing, Aerodynamics Coefficients

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