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
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Outputs
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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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Children:
ACPro: ACPerformance/ComputeAlphaConstantFlightPathAngle
ACPro: ACPointMass/RHS2DPointMass
ACPro: ACPointMass/SimpleLiftAndDrag
ACPro: Airbreathing/Ramjet
ACPro: Airbreathing/Turbofan
ACPro: Airbreathing/Turbofanramjet
Common: Atmosphere/StdAtm
Common: Graphics/Plot2D
Common: Graphics/TimeLabl
Math: Integration/RK45