effective flow area coefficient which had been a function of the valve lift. The flow coefficients at different lifts were determined experimentally and incorporated into the compressor simulation program developed by the same authors. Machu et al. (2004) stated that the calculation of transient flow pulsations had been necessary to obtain
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NACA 0012 lift coefficient at a Reynolds number of 179,000. NACA 0012 drag coefficient at a Reynolds number of 179,000. Whereas the airfoil stalled at 16° at a Reynolds number of 3 million, XFOIL now predicts stall will occur at about 11° and Javafoil indicates a stall angle of only 9°.
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Any aircraft wing is the major component which will play vital role in the generation of lift and at different maneuvering moments throughout the flight. So to maintain this good maneuverability the aircraft wing has to undergo deferent deflections called angle of attack such that the high lift and low drag or vice versa can be settled in the flight.