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Engineering, 11.10.2019 05:30 kaylin28

For a given airfoil, the critical mach number is 0.8. calculate the value of p/p[infinity]. at the minimum pressure point when m[infinity] = 0.8.

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For a given airfoil, the critical mach number is 0.8. calculate the value of p/p[infinity]. at the m...
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