The NACA 64-412 is a cambered aerofoil with lift coefficient given by CL # 0.11a 0.3 when o is in...

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Ста-См e above eauation atates thal う-the-pdehing-moment coefficuut about an ausipdunamic centre rft Y e S a OA) th

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The camber of a thin aerofoil with unit chord is given by the equation:

?(?) = ??(? − 1)(? − ?) where k > 0 and b > 0. Depending on the choice of b, this equation can represent a reflex aerofoil in which the mean camber line curves upward toward the trailing edge. To check whether the aerofoil is reflex, one checks to see whether the above curve has both a maximum and minimum (with the maximum occurring ahead of the minimum). (i) Obtain the value of x where corresponding to maximum camber, and if...
1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow...

1. For the airfoil Cp data shown below; • What is the maximum airspeed in flow just outside the boundary layer if the freestream speed Vo = 120 m/s? • What is the local Mach number at this point if the altitude is 12 km? • What is the approximate value of C, for these conditions? Ans: V = 204.35 m/s, M = 0.693, CL ~ 1.15. -1.00 .. .... -0.50 .... ..... 0 0.1 0.2 0.3 0.4 0.5 0.6...