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Path: ACPro/Airbreathing
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Ramjet model including aerodynamic losses. The default fuel is H2.
Computes the thrust and exhaust velocity including aerodynamic losses.
Inputs u and h must have the same lengths. This function calls the
standard atmosphere model.
if no inputs are given and just one output it will return the default
data structure.
Type Ramjet for a demo. The demo varies the altitude from 10 to 40 km
and the Mach number from 1.5 to 7.
Since version 8.
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Form:
[t, tSFC, uE, f, iSp, thR] = Ramjet( m, d, p )
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Inputs
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m (1,:) Mach number
d (1,1) Data structure
.gamma (1,1) Airflow ratio of specific heats
.qR (1,1) Joules/kg for the fuel (default H2)
.etaB (1,1) Combustion efficiency
.t04 (1,1) Combustor temperature
.cP (1,1) Air specific heat
.pEOverPA (1,1) Ratio of exit pressure to atmospheric pressure
.aI (1,1) Inlet area
.rD (1,1) Diffuser pressure ratio
.rC (1,1) Combustor pressure ratio
.rN (1,1) Nozzle pressure ratio
.aE (1,1) Exit area
.atmData (1,1) Atmosphere data for StdAtm
p (1,1) Standard atmosphere
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Outputs
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t (1,:) Thrust (N)
tSFC (1,:) Thrust specific fuel consumption
uE (1,:) Exhaust velocity (m/s)
f (1,:) Fuel air ratio
m (1,:) Mach number
iSp (1,:) Specific impulse (sec)
thR (1,:) Thrust to mass flow ratio
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Reference: Hill, P.G. and Peterson, C. R., "The Mechanics and
Thermodynamics of Propulsion," Addison-Wesley, Reading,
MA, 1970, pp. 154-157.
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Common: Atmosphere/StdAtm Common: Graphics/Plot2D
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