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  1. E

    tail moment imbalance

    What are the ways to determine Cl?
  2. E

    tail moment imbalance

    L=CL×0.5×ρ×V^2×S I want to design a V tail. The moment of the wing turned out to be -9.3 Nm. The tail needs to balance this moment. I'm thinking of taking the tail moment arm as 0.5-0.6m. I calculate a lift force with the formula I wrote, but my lift force turns out to be very low. Is the...

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