Computer_4_09 - Re for transition as 250,000 to reflect a...

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Computer Assignment #4 We wish to analyze the viscous flow over the top surface of an NACA 4412 airfoil at 1 deg. AoA moving at 100 m/sec. in air at STP. The chord is 0.5152 m. Do you expect laminar or turbulent flow over most of the surface at these conditions? 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. Run the WALZ laminar method for this flow as before. Pick the Flat Plate
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Unformatted text preview: Re for transition as 250,000 to reflect a real flow environment. Look to see if you predict transition or separation. If you predict transition, you need to use a turbulent flow calculation method to complete your analysis. Under File select Launch and pick Launch MOSES at the transition location. Now, you must carefully go through the input in the lower panel in the MOSES window to make the appropriate choices for the items under: Fluid Properties, 2) Reference Properties, 3) Surface Characteristics and 4) Calculation Parameters. Run the MOSES calculation and study the results. Discuss all your results....
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