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N812183

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  • N812183

    The question asks about C(L) and the contributions to it.

    To me C(L) directly depends on the angle of attack and on the characteristics of the aerofoil - camber.
    But the given answer says that for a given value of lift C(L) depends on Q and S.
    But the question doesn't specify constant lift. The Lift formula says L = C(L).Q.S so C(L) as a variable would be a function of alpha and camber first (which is one of the possible answers). If you insist that L is constant then sure, the pilot's actions will cause C(L) to also become a function of Q and maybe S if the flaps are deployed.

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