By R. Varatharajoo, E. J. Abdullah, D. L. Majid, F. I. Romli, A. S. Mohd Rafie
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Extra resources for Aerotech IV: Recent Advances in Aerospace Technologies: Selected, Peer Reviewed Papers from the AEROTECH IV, November 21-22, 2012, Kuala Lumpur, Malaysia
The drag is dominated by flapping effect. Conclusions The present work has been performed to assess the effect of flapping-pitching motion with pitchflap phase lag in the flight of ornithopter. In this conjunction, a computational model has been considered, and a generic computational procedure has been adopted. Two-dimensional unsteady theory of Theodorsen with modifications to account for three-dimensional and viscous effects, leading edge suction and post-stall behavior. The study is carried out on rectangular and semielliptical wing planforms.
M. M. E. F. my d Keywords: vortex trap, flow control, helicopter Abstract. During helicopter forward flight, the retreating blade revolves at high angle of attack compared to advancing blade in order to balance the lift and also to stabilise the helicopter. However, due to the aerodynamics limitations of the retreating blade at forward flight, stall may occur at high angle of attack compared with the advancing blade. This phenomenon is dangerous for pilot when controlling and balancing the helicopter while flying against strong wind.
All atomizers were tested using water at room temperature as working fluid to investigate the air core diameter at different injection pressure. First, water tank is fully filled with water. The water was colored using red dye to get cleared images for air core measurement. Then, it is pumped to the atomizer. The supply water pressure is controlled via a ball valve. The water flow rate (Q) and supply pressure is measured by a digital flow meter and a Bourdon-type pressure gauge respectively. The digital flow meter was pre-calibrated by the manufacturer with an accuracy of ±2% of full scale.