1. A thin airfoil is flying at Mach 2 through air at 12,000 meters ISA, and vibrates in plunge motion with amplitude of 1% of chord. The frequency is 200 cycles per second. The chord is 1 meter. Find the unsteady pressure variation at 3/4 chord. Also find the amplitude of the unsteady lift coefficient, and the phase relative to the plunge motion.

Construct a program (FORTRAN or MatLab) to give these results for given Mach number, plunge amplitude and frequency. Plot the results as functions of reduced frequency, and show that they tend to the low-and high frequency limits properly.

2. Modify this for a sharp-edged gust, whose vertical velocity is equivalent to the amplitude of the plunge motion of the above problem.