Ainsley Rexford | Engineering Portfolio

In this report for MEAM 5450, I compared the coefficient of lift and angle of attack across three different airfoil computation methods: inviscid flow, viscid flow, and using the panel method. I compared these computations across three different airfoil geometries: flap at 85% chord, flap at 70% chord, and no flap. The flap at 85% chord caused the highest amount of drag due to a high spike in drag at an angle of attack of 14 degrees. All three geometries had similar amounts of drag at negative angles of attack but as the angle of attack increased, the slope of the flap at 70% chord increased. On average, a flap at 70% generates the most drag and the flap at 85% closely matches that of the standard airfoil.