Repeat Examples 6 .6 and 6 .7 for the M_∞ = 1 .1 test case reported in Tijdeman et al. (1979b). Are the Mach box and Mach panel method predictions as good as for the M_∞ = 1 .32 case? Are there any numerical instabilities as B → 0 ?

Data from Example 6.6

Calculate the oscillating pressure distribution on the wing of the F-5 aircraft pitching about the half-chord at M_∞ = 1.32.

Data from Example 6.7

Repeat Example 6.6 using the Mach panel method.