<?xml version="1.0"?>
<!--
  File:     BR710.xml
  Author:   Aero-Matic v 0.81

  Inputs:
    name:           Rolls Royce BR710
    type:           turbine
    thrust:         15000 lb
    augmented?      no
    injected?       no

    reference: http://www.togo84.com/spec05_gas_turbines.pdf
           or: http://www.aviationnow.com/media/pdf/spec05_gas_turbines.pdf
    --------------------------------------------------------
    type: ..............................   A-F
    no. fan stages: ....................     1
    no. compressor stages: .............    10
    no. turbine stages lp: .............     2
    no. turbine stages hp: .............     2
    compressor type: ...................    An
    max power at sea level: ...........  15000 lb
    specific fuel consumption at max power:  0.639
    overall pressure ratio at max power:    24
    max envelope diameter: .............    48 in
    max envelope length: ...............   134 in
    dirty weight (wo. tailpipe): .......  3600 lb
-->

<turbine_engine name="BR710">
  <milthrust> 15000.0 </milthrust>
  <bypassratio>     4.2 </bypassratio>
  <tsfc>            0.639 </tsfc>
  <bleed>           0.03</bleed>
  <idlen1>         30.0 </idlen1>
  <idlen2>         60.0 </idlen2>
  <maxn1>         100.0 </maxn1>
  <maxn2>         100.0 </maxn2>
  <augmented>         0 </augmented>
  <injected>          0 </injected>

  <function name="IdleThrust">
   <table>
    <independentVar lookup="row">velocities/mach</independentVar>
    <independentVar lookup="column">atmosphere/density-altitude</independentVar>
    <tableData>
         -10000     0     10000   20000   30000   40000   50000   60000
     0.0  0.0430  0.0488  0.0528  0.0694  0.0899  0.1183  0.1467  0.0
     0.2  0.0500  0.0501  0.0335  0.0544  0.0797  0.1049  0.1342  0.0
     0.4  0.0040  0.0047  0.0020  0.0272  0.0595  0.0891  0.1203  0.0
     0.6  0.0     0.0     0.0     0.0     0.0276  0.0718  0.1073  0.0
     0.8  0.0     0.0     0.0     0.0     0.0474  0.0868  0.0900  0.0
     1.0  0.0     0.0     0.0     0.0     0.0     0.0552  0.0800  0.0
    </tableData>
   </table>
  </function>

  <function name="MilThrust">
   <table>
    <independentVar lookup="row">velocities/mach</independentVar>
    <independentVar lookup="column">atmosphere/density-altitude</independentVar>
    <tableData>
          -10000       0   10000   20000   30000   40000   50000   60000
     0.0   1.2600  1.0000  0.7400  0.5340  0.3720  0.2410  0.1490  0.0
     0.2   1.1710  0.9340  0.6970  0.5060  0.3550  0.2310  0.1430  0.0
     0.4   1.1500  0.9210  0.6920  0.5060  0.3570  0.2330  0.1450  0.0
     0.6   1.1810  0.9510  0.7210  0.5320  0.3780  0.2480  0.1540  0.0
     0.8   1.2580  1.0200  0.7820  0.5820  0.4170  0.2750  0.1700  0.0
     1.0   1.3690  1.1200  0.8710  0.6510  0.4750  0.3150  0.1950  0.0
     1.2   1.4850  1.2300  0.9750  0.7440  0.5450  0.3640  0.2250  0.0
     1.4   1.5941  1.3400  1.0860  0.8450  0.6280  0.4240  0.2630  0.0
    </tableData>
   </table>
  </function>

</turbine_engine>

