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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.

What two relations do you use for pressure coefficient, to determine the critical Mach number of an airfoil?

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* 4. What two relations do you use for pressure coefficient, to determine the critical Mach number of an airfoil?

How does knowing the incompressible-flow pressure distribution help in determining the critical Mach number?

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* 5. How does knowing the incompressible-flow pressure distribution help in determining the critical Mach number?

Why does the supersonic flow region above an airfoil beyond critical Mach number stay confined to a small region?

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* 6. Why does the supersonic flow region above an airfoil beyond critical Mach number stay confined to a small region?

What is a lambda shock, and how is it formed?

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* 7. What is a lambda shock, and how is it formed?

In a Mach 2 flow, what is the limiting sweep angle dividing the zone of "supersonic leading edge" from "subsonic leading edge"?

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* 8. In a Mach 2 flow, what is the limiting sweep angle dividing the zone of "supersonic leading edge" from "subsonic leading edge"?

How is the Drag Divergence Mach number different from the Critical Mach number?

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* 9. How is the Drag Divergence Mach number different from the Critical Mach number?

What happens to the pitching moment on an airfoil, at a given angle of attack, as it accelerates from below the critical Mach number, through to fully supersonic flow? Explain from physical reasoning.

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* 10. What happens to the pitching moment on an airfoil, at a given angle of attack, as it accelerates from below the critical Mach number, through to fully supersonic flow? Explain from physical reasoning.

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