* 1. Please think how you learned this section. What did you find to be helpful? Please tick all that apply.

* 2. Please list the top 5 concepts that you learned in this module.

* 3. What concepts pose(d) difficulties for you? Please discuss, and also how you solved the difficulty if you did.

* 4. What transformation do you use to reduce the compressible flow over a wing to the Laplace equation?

* 5. How does the corresponding incompressible-flow wing compare in aspect ratio to the original compressible-flow wing?

* 6. Compare the lift on a wing of aspect ratio 5 at a given angle of attack at Mach 0.7 at 12000 meters ISA, to that on the equivalent wing tested at Mach 0.2 at sea level standard conditions.

* 7. Discuss the logic involved in solving for the drag of a pointed body of revolution in supersonic flow using Karman's source method.

* 8. What is the slender wing analysis approach of R.T. Jones? Why is it adequate to consider the cross-flow in a plane to solve this problem?

* 9. What is the general approach to solving for the lift of a wing of moderate aspect ratio (not large enough for lifting line, not slender enough for slender-wing theory).

* 10. How is the Sears-Haack body shape different from that of two Karman ogives placed base-to-base, with the base area being the same as the maximum cross-sectional area of the Sears-Haack body?