TurboRamjetSim:

deprecated

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   Simulates a turboramjet engine on a fixed flight path angle trajectory.
   It transitions from turbofan to ramjet at d.mTransition
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   Form:
   mFuel = TurboRamjetSim( x, tEnd, dT, d, plott )
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   ------
   Inputs
   ------
   x           (5,1)  [v;gamma;h;m;range]
   tEnd        (1,1)  End time
   dT          (1,1)  Time step
   d           (1,1)  Data structure
   alpha       (1,n)  Angle of attack history
   plott       (1,1)  1 = plot, 0 = no plot

   -------
   Outputs
   -------
   mFuel       (1,:)  Mass of fuel consumed (kg)
   machNo      (1,1)  Final Mach number
   x           (5,1)  Final state vector
   xP          (8,:)  Plotting data [x;machNo;alpha;q;drag]
   t           (1,1)  Final time

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Children:

ACPro: ACPerformance/ComputeAlphaConstantFlightPathAngle
ACPro: ACPointMass/RHS2DPointMass
ACPro: ACPointMass/SimpleLiftAndDrag
ACPro: Airbreathing/Turbofanramjet
Common: AtmosphericCalculations/StdAtm
Common: Database/Constant
Common: Graphics/Plot2D
Common: Graphics/TimeLabl
Common: Math/RK45