Question

A very thin flat plate "airfoil" with a 1m chord is placed at an angle of attack α with respect to the free stream velocity Voo. The pressure distribution on the top and bottom surfaces of the "airfoil" are given by: pu -5.4x104 + 4x104(x - 1)2 (Nm2) pi- 1.7x105 + 2x104(x - 1)2 (Nm2) where X is the distance from the leadıng edge measured in meters. Neglecting shear stresses, determine the lift and drag forces per unit span. At what location does the pressure distribution not have a net moment, ie what is the location of the center of pressure? Also determine the moments about the leading edge and the quarter- chord point (x-0.25m here as the chord is 1m) LE Pu(x) p,(x)

Answer 1

Solb lotol normel andoxiaJ fores pe unttpan anu v en Te LE LSE re L E LE Heuteノ one ^ledes TG LE LE- Le

hin Since, the plot, นั้, Hẳn lc (Pu.%)y.dy:c inte , lhsnn strens an negli gible, LE Le eodiv edae cfu Chordn ep..-Le N' L-s.cno" Co sox