Applied Aerodynamics Matlab Problem Write a Vortex Lattice p

Applied Aerodynamics (Matlab Problem)

Write a Vortex Lattice program in Matlab to calculate the lift and induced drag of a planar wing (no twist or camber). Write your program so that the inputs are the wing aspect ratio, taper ratio, sweep angle at the 1/4 chord and angle of attack and return both CL and CDi. Use atleast 20 spanwise and 5 chordwise panels.

a) For a fixed angle of attack of 4 degrees, aspect ratio of 8 and zero sweep to show the variation in L/D with taper ratio over a range of 0.2 to 1.0.

b) For a fixed angle of attack of 4 degrees, aspect ratio of 8 and taper ratio of 0.5, show the variation in L/D with sweep angles over a rangle of -25 to +35 degrees.

Solution

a)

CL = 4 * 8   + 0.2 * 8

CL = 33.6

CDi = 4*8 - 0.2*8

CDi = 30.4