jsbsim.js/JSBSim/engine/AJ26-33A.xml

JSBSim flight dynamics model ported to JavaScript

<?xml version="1.0"?>
<!--
  File:     AJ26-33A.xml
  Author:   Aero-Matic v 0.8; refined by Jon Berndt

  Inputs:
    Name:           AJ26-33A (Aerojet)
    Type:           rocket
    Thrust:         339000.0 lb
    Propellants     LO2/HC (LOX Kerosene)
    Propellant flow rate (est.): 1130 lbs/sec (lbs weight - not mass)
    Mixture Ratio   2.6 (by mass, Ox/Fuel)
    Ox. Flow Rate (SL) 816
    Fuel Flow Rate (SL) 314
    Lox-HC Mol Wt.  22
    Flame temp      3200+ K (~5300 Fahrenheit)
    Chamber Pressure 2109 psia (303,700 psf)
    ISP (sea level) 297
    ISP (vacuum)    331
    Weight          2725 lbm
    Thrust Weight   125
    Length/Diameter 12.2/6.7 feet
    Nozzle Exp. Ratio 27:1
    Nozzle exit velocity 5920 ft/sec
    Nozzle exit pressure 14.7 psi (2117 psf)

    Molecular mass of HC (Kerosene): 175

    Throttleable Control  55% - 104%
    Mixture Ratio Control  Yes
    Status Flight Qualified

-->

<rocket_engine name="AJ26-33A">
  <isp>                   331.0 </isp>
  <maxthrottle>           1.00  </maxthrottle>
  <minthrottle>           0.40  </minthrottle>
  <slfuelflowmax unit="LBS/SEC">  314.0  </slfuelflowmax>
  <sloxiflowmax unit="LBS/SEC">   816.0  </sloxiflowmax>
</rocket_engine>