Finding required thrust power for jet engine aircraft.

  1. nah

    nah 1

    1. The problem statement, all variables and given/known data
    I need to find required thrust power for lockeed s3a. I know Thrust=Drag in horizontal flight.
    For take off, need to use the take off angle, split the Weight (G) into 2 components using the takeoff angle... Same for landing.

    Given:
    G=19278kg ---> 19278*9.81=189,1kN
    V=814kph
    Wing area=22m(in square)
    Expluatational overload = 4

    2. Relevant equations
    G=Y ; G=weight, Y= Lift
    T=Q ; T= thrust, Q=drag

    Q=0.5Cx*(air density)*S*(v in sq)

    I dont have the Cx...


    3. The attempt at a solution


    expluatational overload = (P-Q)/G

    Anyhow i was thinking, if theres a way to calculate the required thrust using airspeed?
    Btw in wikipedia it shows the Thrust for that aircraft is 2*41.26kN
     
  2. jcsd
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