Test results obtained on a NACA 23012 airfoil show the following data: ао C₁ 0 0.15 9 1.20 If this airfoil is used in the design of an elliptical wing with aspect ratio, A=7.0, determine the wing lift curve slope at low Mach numbers.

Test results obtained on a NACA 23012 airfoil show the following data: ао C₁ 0 0.15 9 1.20 If this airfoil is used in the design of an elliptical wing with aspect ratio, A=7.0, determine the wing lift curve slope at low Mach numbers.

Elements Of Electromagnetics

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ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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Question

4.2
Test results obtained on a NACA 23012 airfoil show the following data:
aº
C₁
0
0.15
9
1.20
If this airfoil is used in the design of an elliptical wing with aspect ratio, A=7.0, determine
the wing lift curve slope at low Mach numbers.

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