|
SUPPORT SITE |
|
|
|
SUPPORT SITE |
|
Path: ACPro/Airbreathing
--------------------------------------------------------------------------
Ramjet jet engine model producing thrust and specific fuel consumption.
Type RamjetKerrebrock for a demo.
Since version 2014.1
--------------------------------------------------------------------------
Form:
[t, iSp, tS] = RamjetKerrebrock( m, d, p )
d = RamjetKerrebrock;
--------------------------------------------------------------------------
------
Inputs
------
m (1,:) Mach number
d (1,1) Data structure for engine
.gamma (1,1) Specific heat ratio of air
.cP (1,1) Specific heat of air
.qR (1,1) Heating value of fuel
.tT4 (1,1) Temperature at station 4
.aInlet (1,1) Inlet area
p (1,1) Standard atmosphere
-------
Outputs
-------
t (1,:) Thrust (N)
iSp (1,:) Specific impulse (s)
tS (1,:) Specific thrust
--------------------------------------------------------------------------
Reference: Kerrebrock, J.
http://web.mit.edu/16.unified/www/FALL/thermodynamics/notes/node85.html
--------------------------------------------------------------------------
Common: Atmosphere/StdAtm Common: Graphics/Plot2D
Back to the ACPro Module page