Lift coefficient at start of range calculator

lift coefficient at the start of the range for an aircraft, you generally need more specific information about the aircraft’s aerodynamic characteristics, flight conditions, and mission profile. However, I can provide you with a general overview of how you might approach this calculation and the factors that come into play.

Cl=w/(0.5*ρ*v^2*s)

  • Cl: Lift coefficient, a dimensionless value that represents the ratio of lift to dynamic pressure and wing area.
  • w: Aircraft weight, typically given in newtons or pounds.
  • ρ: Air density, which varies with altitude and temperature.
  • v: Airspeed of the aircraft.
  • s: Wing reference area, typically in square meters or square feet.

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