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Lift Formula

  1. Oct 5, 2009 #1
    You are flying an F-117A fully equipped, which means that your aircraft weighs 52,500 pounds. You want to maintain equilibrium in straight and level flight at an altitude of 30,000 feet, cruising at 400 knots to conserve fuel. The aircraft's wing area is 1,140 square feet. At what angle of attack should the F-117A be set to maintain equilibrium?
    The air density at FL300 is .000889


    This was an assignment (independent study) assigned in math. I am working on it however I felt I completed the problem properly, however the answer seems to disagree with me.


    L = (1/2) d v2 s CL

    * L = Lift, which must equal the airplane's weight in pounds
    * d = density of the air. This will change due to altitude. These values can be found in a I.C.A.O. Standard Atmosphere Table.
    * v = velocity of an aircraft expressed in feet per second
    * s = the wing area of an aircraft in square feet
    * CL = Coefficient of lift , which is determined by the type of airfoil and angle of attack.




    52,500 = (1/2) (.000889) (400^2 ) (1140) CL

    52,500 = (81076.8) CL

    0.648 = CL


    I'm not concerning significant digits.
     
  2. jcsd
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