EXIT THIS SURVEY Exit this survey Subject content: Wings and Bodies in Compressible Flow 1. * 1. Please think how you learned this section. What did you find to be helpful? Please tick all that apply. 1. Read the Powerpoint notes. 2. Wrote down the notes on paper to see if you agreed with the logic 3. Read the textbook 4. Tried the examples in the Solved Problems library 5. Solved old tests given by the instructor 6. Asked friends * 2. Please list the top 5 concepts that you learned in this module. 1. 2. 3. 4. 5. * 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? Done