Aircraft Aerospace Aerodynamics Formulas

Solving For Lift Force

coefficient of lift (C_{L})

= 0

= 0

density (p)

= 0

= 0

kilogram/meter^3

velocity (V)

= 0

= 0

meter/second

surface area (A)

= 0

= 0

meter^2

lift force (L)

= NOT CALCULATED

Select to solve for a different unknown

Aircraft and airplane wing lift equations

Solve for lift force | |

Solve for lift coefficient | |

Solve for air density | |

Solve for velocity | |

Solve for lift surface area |

Where

L | = | lift force |

C_{L} | = | lift coefficient |

p | = | air density |

V | = | velocity |

A | = | lift surface area |

Reference - Books:

1) Munson, B.R., D. F. Young, and T. H. Okiishi. 1994. Fundamentals of Fluid Mechanics. John Wiley and Sons, Inc. 2nd ed.

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