TurboRamjetSim:

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   Simulates a turboramjet engine on a fixed flight path angle trajectory.
   It transitions from turbofan to ramjet at d.mTransition.

   Type TurboRamjetSim for a demo.

   Since version 1.0.
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   Form:
   d = TurboRamjetSim;
   [mFuel,machNo,x,xP,t] = TurboRamjetSim( x, tEnd, dT, d, plott )
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   Inputs
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   x           (5,1)  [v;gamma;h;m;range]
   tEnd        (1,1)  End time
   dT          (1,1)  Time step
   d            (.)   Data structure
                      .engine       (.)  Engine data
                      .machEnd     (1,1) Mach end condition 
                      .altitudeEnd (1,1) Altitude end condition
                      .atmData      (.)  For StdAtm
                      .cDCL         (f)  Function handle
                      .tFcn         (f)  Function handle
                      .rP          (1,1) Planet radius (m)
                      .g           (1,1) Gravity (m/s2)
                      .aero         (.)  Aero data structure   
                      .constrainGamma    Flag
   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
   xP          (7,:)  [x;machNo;alpha];
   t           (1,:)  Time vector for xP

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   See also Ramjet, Turbofan, SimpleLiftAndDrag, Turbofanramjet,
   ComputeAlphaConstantFlightPathAngle, RHS2DPointMass
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