Unformatted text preview: the location of the max camber? What tells you the value of the max camber? What are the values of these quantities for the 2414? b) The geometry of the NACA 4 series is coded in the Matlab function naca4.m, available in the HW9 directory. (The formulas coded there are from Abbott & von Doenhoff). The basic shape has a “chopped off” trailing edge. What is the thickness of that TE (in units of the chord length)? Why is it chopped? c) The naca4 function has a closure option, which removes the chopped off TE by slightly altering the aft of the airfoil to a point. Compare the open and closed shapes… especially near the TE. d) Calculate the pressure distribution on the NACA2414 at 10deg aoa, using both the “open” and “closed” shapes. Examine the pressure distribution near the TE in particular. What’s the difference? e) Calculate the lift coefficient by using the KuttaJoukowski law. Also calculate it by direct integration of the pressure. Do you get the same answer?...
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 Fall '09
 Lift, Airfoil, Angle of attack, camber, incompressible potential flow, source/vortex panel method

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