Problem 1 40 points Consider a NACA 1408 airfoil The mean ca

Problem 1. (40 points) Consider a NACA 1408 airfoil. The mean camber line for this airfoil is given by NACA 4 digit airfoil specification This NACA airfoil series is controled by 4 digits e.g. NACA 2412, which designate the camber, position of the maximum camber and thickness. If an airfoil number is NACA MPXX NACA 2412 then Mis the maximum camber divided by 100. In the example M 2 so the camber is 0.02 or 2% of the chord P is the position of the maximum camber divided by 10. In the example P 4 so the maximum camber is at 0.4 or 40% of the chord. XX is the thickness divided by 100. In the example XX 12 so the thickness is 0.12 or 12% of the chord. NACA 4 digit airfoil calculation The NACA airfoil section is created from a camber line and a thickness distribution plotted perpendicular to the camber line. The equation for the camber line is split into sections either side of the point of maximum camber position (P). In order to calculate the position of the final airfoil envelope later the gradient of the camber line is also required. The equations are: Front (0 sx

Solution

Using the given relations, for 1402 foil camber is .01 of chord, maxm at .4 of chord, thicknes 2%

angle at zero lift can be calculated by second methods, giving   alpha0 = 1/2 ( A0+A1)

Need to compute the integrals given the camber line. get A0 and A1

2) lift coeff   2pi( 5deg - alpha 0)

3) Cm at 5 deg pi/4( A2-A1)

The hand calculations are tedious. Program i and do it. A brilliant PhD scholar likeyou can do this wihout asking others to do it.