Question

What is the coefficient of lift (CL) of an airfoil with a lift of 1200 N, wing area of 56 m2 , p (air density) of 1.225 kg/m2 and a velocity of 10 m/sec? Round to 2 decimal places.

Answer 1

The coefficient of lift (CL) of an airfoil with the given parameters is calculated to be 0.35 when rounded to two decimal places.

Step-by-step explanation:

The coefficient of lift (CL) can be calculated using the lift equation: CL = L / (0.5 × p × V² × A), where L is the lift force, p is the air density, V is the velocity relative to the airfoil, and A is the wing area.

Plugging in the values given: CL = 1200 N / (0.5 × 1.225 kg/m³ × (10 m/s)² × 56 m²).

Performing the calculation yields:

CL = 1200 / (0.5 × 1.225 × 100 × 56) = 1200 / (0.6125 × 5600) = 1200 / 3430 = 0.349854

Therefore, the coefficient of lift (CL) rounded to two decimal places is 0.35.