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The lift FLF_L on an airfoil depends on the aircraft speed VV, the speed of sound cc, the fluid density, the airfoil chord length lcl_c, the airfoil thickness tt, and the angle of attack α\alpha. Find an expression for FLF_L.

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In this exercise, we are asked to derive an expression for the lift FLF_L produced by an airfoil. The given variable parameters are listed below:

  • FLF_L - lift force
  • VV - velocity
  • cc - speed of sound
  • ρ\rho - fluid density
  • lcl_c - airfoil chord length
  • tt - airfoil thickness
  • α\alpha - angle of attack

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