Computer _2(2009)

Computer _2(2009) - Surface Properties window. Note that...

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Computer Assignment #2 We wish to analyze the viscous flow over the top surface of an NACA 4412 airfoil at 1 deg. AoA moving at 10 m/sec. in air at STP. The chord is 0.5152 m. Use the Vortex Panel Method in the engapplets Web site to calculate the inviscid flow. From that solution, you need the surface velocity distribution on the upper surface: s,U(upper). Select and copy this file. This will be the edge velocity distribution for the boundary layer calculation. Use the WALZ code in the engapplets under Boundary Layer and Convection Applets Web site to calculate the boundary layer flow. Paste the inviscid edge velocity distribution into the
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Unformatted text preview: Surface Properties window. Note that this flow has a rounded leading edge. You should get a sensible looking velocity distribution in the top of the panel in the WALZ window after you set Maximum x/L=1.0. Now, you must carefully go through the input in the lower panel in the WALZ window. You must make the appropriate choices for the items under: Fluid Properties, 2) Reference Properties, 3) Surface Characteristics and 4) Calculation Parameters. Leave the last item as the Default value. We will discuss this item later....
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This note was uploaded on 01/23/2012 for the course AOE 3044 taught by Professor Schetz,j during the Fall '08 term at Virginia Tech.

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