A \(45^{\circ}\) sweep angle delta wing is in the supersonic flow with \(\mathrm{M}=1.5\).

(i) Divide the half of the wing with equally sized 25 boxes and give identification numbers for the boxes ranging from 1 to 25 .

(ii) Use sufficient number of same size boxes to discretize the upstream Mach cone and number them separately with double digits. (use Fig. 5.16 as a sample).

(iii) Form the \(\mathrm{R}+\mathrm{i}\) I influence coefficient matrix as a \(25 \times 25\) matrix which shows the effect of each box in the upstream Mach cone to the box on the wing.

Fig. 5.16

Transcribed Image Text:

M , (x,y) Upstram Mach cone y,n (x,y)