Last Updated On [03-11-2023]
Which of the following airfoil will have location of the maximum camber at half chord length from the leading edge?
(A) NACA 5212
(B) NACA 1225
(C) NACA 2215
(D) $\operatorname{NACA} 2512$
Question ID - 155627 :- Which of the following airfoil will have location of the maximum camber at half chord length from the leading edge?
(A) NACA 5212
(B) NACA 1225
(C) NACA 2215
(D) $\operatorname{NACA} 2512$
Which of the following airfoil will have location of the maximum camber at half chord length from the leading edge?
(A) NACA 5212
(B) NACA 1225
(C) NACA 2215
(D) $\operatorname{NACA} 2512$
Next Question :
For a laminar incompressible flow past a flat plate at zero angle of attack, the variation of skin friction drag coefficient $\left(\mathrm{C}_{\mathrm{f}}\right)$ with Reynolds number based on the chord length $\left(\mathrm{Re}_{\mathrm{c}}\right)$ can be expressed as
(A) $C_{f} \propto \sqrt{\operatorname{Re}_{c}}$
(B) $\mathrm{C}_{\mathrm{f}} \propto \mathrm{Re}_{\mathrm{c}}$
(C) $\mathrm{C}_{\mathrm{f}} \propto 1 / \sqrt{\mathrm{Re}_{\mathrm{c}}}$
(D) $C_{f} \propto 1 / \operatorname{Re}_{c}$
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