Question

and drag of the wing if the airplane is cruising at 130 knots at 5,500 feet under standard conditions. 5.15 A flat plate is oriented at an angle of attack of 90° to the flow in a low-speed wind tunnel. Assume the pressure over the front of the plate is constant and equal to the stagnation pressure. Assume the pressure on the reward facing side is also constant but equal to the free stream static pressure. Since the flat plate is perpendicular to the flow, the resulting drag is primarily pressure drag as opposed to skin friction drag. Show that the drag coefficient for this flow is Co-1

Answer 1

Wnk the Bvooulli Pressure due o an Acvodynamf) Onthe Backfoto the plak. CEL) back D-foot- tback.

2 Naa the Draq and c D aa Coeffaent this flow or a flat plat is d