GATE_AE_2027_MOCK_05_Q17 GATE 2027 Aerospace Engineering All-India Master Mock 05 (High-Yield Comprehensive Grand Finale) NAT · 1 Mark
Aerodynamics & Fluid Mechanics • Airfoil & Wing Theory • Thin Airfoil Theory & Camber Effects

For a flat-plate symmetric airfoil of chord c = 1 m in low-speed flow at angle of attack lpha = 0.10 rad, what is the section lift coefficient C_l? (Take 2*pi ≈ 6.2832, round to two decimal places).

Answer Key:
0.63

Step-by-Step Verified Solution

### Solution: C_l = 2\pi lpha = 6.2832 * 0.10 ≈ 0.628 ≈ 0.63. Correct: 0.63 (range 0.61 to 0.65).
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