The figure on the right shows an approximated pressure distribution on an airfoi

Question

The figure on the right shows an approximated pressure distribution on an airfoil and the direction of incoming flow. a. Find the center of pressure for the upper surface of the airfoil (in terms of %chord from the leading edge) b. Find the center of pressure for the bottom surface of the airfoil (in terms of %chord from the leading edge) c. Compute the Lift produced by the airfoil d. Find the pitching moment about the leading edge. Is it nose-up or nose down? The figure on the right shows an approximated pressure distribution on an airfoil and the direction of incoming flow. a. Compute Lift produced by the airfoil b. Compute Drag produced by the airfoil c. Compute Lift Coefficient from (a) and Drag Coefficient from (b) if the airspeed is 0.5 m/sec at sea level density

Explanation / Answer

a) center of pressure at the upper surface of airfoil Pu= P+ 2CpU^2

using pressure coefficient Cp and velocity U we get the value

where P=3N/m

b) at bottom surface we use the same expression but P=1N/m to get the Pl

Pl= 1+ 2CpU^2

c) The produced lift C=2L/U^2bc

using L=1m, using airfoil span b and chord c we get the value

C=2/U^2bc

9a) Lift of the air foil C=2L/U Sin 10^2bc

b) drag force D=Cd*2LU^2

where Cd is the drag coefficient

c) Cl= Lift/2*1*1*.5^2=lift/.5

Cd=D/2*1*1*.5^2 =drag/.5

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