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On a typical aerofoil, a point exists about which the resultant aerodynamic pitching moment M is independent of incidence. This special point is called the Aerodynamic Centre (AC). The numerical value of the pitching moment about AC is denoted MAC. For standard aerofoils in subsonic flows, the Aerodynamic Centre lies approximate ¼ of the chord behind the leading edge (i.e. h=xAC/c ≈ ¼). For supersonic flows, the AC moves abruptly aft to around h ≈ ½; see Fig. 2.2-1. Since MAC is approximately constant over a wide range of CL including zero, MAC is sometimes referred to as the zero-lift pitching moment and denoted M0.
Hi. I am a final year student seeking help with my project. I am supposed to make a device that can detect the eye state of a person to determine whether he/she is sleepy/drowsy, P
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We now have some idea about what models are available to simulate the flow over an aerofoil, and also how to use the Hanley package to apply these methods. Keep referring to you
i want to do project in the area wing in aircraft...please give some sugestions or ideas in that
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