Explain in your own words how a sharp convex corner is able to isentropically expand a supersonic flow. 2. What happens to the Mach angle of a flow as it is expanded and as it is compressed? How does this affect the behavior for sharp, concave corners? 3. How is the Prandtl-Meyer angle defined, and how are we able to make use of that in our calculations? 4. Consider supersonic flow over a triangular airfoil as depicted in the figure below. Calculate the lift and drag coefficients