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 100% of survey complete.
Please think how you learned this section. What did you find to be helpful? Please tick all that apply.

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

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

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

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

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

Why is it appropriate to use the Prandtl-Meyer procedure to deal with compression turns in supersonic flow?

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#### * 4. Why is it appropriate to use the Prandtl-Meyer procedure to deal with compression turns in supersonic flow?

How is the expression for pressure coefficient in supersonic flow different from that in subsonic flow? Why can't the one be used instead of the other?

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#### * 5. How is the expression for pressure coefficient in supersonic flow different from that in subsonic flow? Why can't the one be used instead of the other?

What does the lift coefficient in supersonic flow depend on? Why?

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#### * 6. What does the lift coefficient in supersonic flow depend on? Why?

At what Mach number does the lift curve slope of an airfoil in supersonic flow equal the ideal lift curve slope in incompressible flow? What happens at higher and lower Mach numbers?

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#### * 7. At what Mach number does the lift curve slope of an airfoil in supersonic flow equal the ideal lift curve slope in incompressible flow? What happens at higher and lower Mach numbers?

How do you determine drag of an airfoil in supersonic flow?

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#### * 8. How do you determine drag of an airfoil in supersonic flow?

How do we use the linearized potential equation to solve for the lift and pitching moment of a wing in supersonic flow?

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#### * 9. How do we use the linearized potential equation to solve for the lift and pitching moment of a wing in supersonic flow?

Where is the center of pressure of an airfoil in supersonic flow?