RamjetH2:
renamed
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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
Type
RamjetH2
for a demo. The demo varies the altitude from 10 to 40 km and the Mach
number from 1 to 4.5.
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Form:
[t, tSFC, uE, f, M, iSp, thR] = RamjetH2( u, h, d )
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Inputs
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u (1,:) Velocity (m/s)
h (1,:) Altitude (m)
d (1,1) Data structure
.gamma (1,1) Airflow ratio of specific heats
.etaB (1,1) Combustion efficiency
.qR (1,1) Joules/kg for the fuel (default H2)
.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
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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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Children:
Common: AtmosphericCalculations/StdAtm
Common: Graphics/Plot2D
