Matlab

(given equation to use for Coding)

Please help.

The flow about a thin cambered airfoil shown in Figure 1 can be approximated by potential flow theory. The chord of the airfoil extends along the z-axis from z 0 to T c and is represented by a vortex sheet placed along the chord. The strength per unit of length, r(z), of this vortex sheet is given by OO An sin (mb) sin 0 where is an auxiliary variable related to x as 1 cos 0), 0 S 0 S TT Camber line zCx) Chord The flow about a thin cambered airfoil shown in Figure 1 can be approximated by potential flow theory. The chord of the airfoil extends along the z-axis from z 0 to T c and is represented by a vortex sheet placed along the chord. The strength per unit of length, r(z), of this vortex sheet is given by OO An sin (mb) sin 0 where is an auxiliary variable related to x as 1 cos 0), 0 S 0 S TT Camber line zCx) Chord