Aerospace Engineering > GATE 2026 > Thin Airfoil Theory
Thin airfoil theory predicts the zero-lift angle of attack αL=0 of NACA 2412 airfoil as −2.1°. The corresponding prediction of αL=0 for NACA 5410 airfoil is ________ degrees (rounded off to 1 decimal place).
Correct : -2.6
Similar Questions
The rate of change of moment coefficient with respect to the angle of attack, dCm/dα , at half chord point of a thin airfoil, as per approximations from t...
For a thin flat plate at 2 degrees angle of attack, the pitching moment coefficient about the trailing edge is
For a thin flat plate at 2 degrees angle of attack, the pitching moment coefficient about the trailing edge is
Total Unique Visitors
Loading......