AAE333 Fall 2011 Homework 14 Due: Mon Dec 12 Consider a NACA 006 airfoil with a Re of 10,000 and an angle of attack of 0. You saw in HW13 that XFLR5 gives a solution that is entirely laminar, and with a BL thickness not too different from the flat plate solution. XFLR5 (like its basis XFOIL) uses an “integral method” to do the boundary layer calculation. The simplest integral method is due to Thwaites: http://www.desktop.aero/appliedaero/blayers/lambl.html http://www.scribd.com/doc/39868582/Thwaites-method which I will also talk about in class on Friday Dec 1 (XFLR5 uses a more elaborate method that is claimed to handle mild separation better than Thwaites). Take the invisicid pressure distribution on the NACA006 airfoil (given by XFLR5), and calculate the development of displacement thickness, momentum thickness and skin friction coefficient along the upper surface of the airfoil (the lower surface is the same since the aoa is 0). Compare this to the corresponding
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