Write a MATLAB function to calculate the lift force acting on an airfoil given the air density, wing area, velocity of the airflow, and lift coefficient. Use the formula: L=0.5×ρ×V^2×S×CL​
where:
  • L is the lift force (N)
  • ρ is air density (kg/m³)
  • V is velocity (m/s)
  • S is wing area (m²)
  • CL​ is lift coefficient (dimensionless)
Solve

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Last Solution submitted on Jun 06, 2026

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Chris Cleveland Pauli Huusari Riccardo G. Lorenzo

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