[Jsbsim-cvslogs] CVS: JSBSim/aircraft/DHC6/Engines PT6A-27.xml, NONE, 1.1 Propeller.xml, NONE, 1.1

[Erik H. <eh...@us...>]

Update of /cvsroot/jsbsim/JSBSim/aircraft/DHC6/Engines
In directory sfp-cvs-1.v30.ch3.sourceforge.com:/tmp/cvs-serv7528/Engines

Added Files:
	PT6A-27.xml Propeller.xml 
Log Message:
Split up systems files, add a proper turbine engine and small modifcations to the FDM

--- NEW FILE ---
<?xml version="1.0"?>

<!--
  File:     PT6A-27.xml
  Author:   AeromatiC++ v 3.3.1

  See: http://wiki.flightgear.org/JSBSim_Engines#FGTurboprop

  Inputs:
    name:                   PT6A-27
    type:                   Turboprop Engine
    power:                  680.0 hp
    inlet temperature:      994.0 degrees C
    overall pressure ratio: 6.3:1

  Outputs:
    psfc:                   0.615 lbs/hr/hp
    engine weight:          368.9 lbs
    engine length:          5.1 ft
    engine diameter:        1.9 ft
-->

<turboprop_engine name="PT6A-27">
  <milthrust unit="LBS">       1523.2   </milthrust>
  <idlen1>                       60.0   </idlen1>
  <maxn1>                       100.0   </maxn1>
  <maxpower unit="HP">          680.0   </maxpower>
  <psfc unit="LBS/HR/HP">         0.615 </psfc>
  <n1idle_max_delay>              1     </n1idle_max_delay>
  <maxstartingtime>              20     </maxstartingtime>
  <startern1>                    20     </startern1>
  <ielumaxtorque unit="FT*LB"> 1629.3   </ielumaxtorque>
  <itt_delay>                     0.05  </itt_delay>
  <betarangeend>                 64     </betarangeend>
  <reversemaxpower>              60     </reversemaxpower>

  <function name="EnginePowerVC">
    <table>
      <description> Engine power, function of airspeed and pressure </description>
      <independentVar lookup="row">atmosphere/P-psf</independentVar>
      <independentVar lookup="column">velocities/ve-kts</independentVar>
      <tableData>
              0      50     100    150    200    250    300    350
        503   0.357  0.380  0.400  0.425  0.457  0.486  0.517  0.550
       1048   0.586  0.589  0.600  0.621  0.650  0.686  0.724  0.764
       1328   0.707  0.721  0.731  0.757  0.786  0.821  0.858  0.896
       1496   0.779  0.786  0.808  0.821  0.857  0.900  0.945  0.993
       1684   0.850  0.857  0.874  0.900  0.943  0.979  1.016  1.055
       1896   0.914  0.929  0.946  0.971  1      1.057  1.117  1.181
       2135   1      1.011  1.029  1.043  1.083  1.150  1.221  1.297
       2213   1.029  1.043  1.057  1.079  1.114  1.171  1.231  1.294
     </tableData>
   </table>
  </function>

  <table name="EnginePowerRPM_N1" type="internal">
    <description> Engine Power, function of RPM and N1 </description>
    <tableData>
              0       5       60      86      94      95      96      97      98      99     100     101
      0.0     0.0     0.5     0.5     0.5     0.5     0.5     0.5     0.5     0.5     0.5     0.5     0.5
    853.7     0.0     0.5    32.0   183.1   320.3   347.8   384.4   421.0   457.6   485.0   530.8   567.5
   1278.2     0.0     0.5    27.5   210.5   366.1   393.5   430.2   462.2   503.3   540.0   585.8   622.3
   1705.1     0.0     0.5     4.6   219.6   402.7   434.7   466.8   503.3   544.5   576.6   622.3   658.9
   2131.9     0.0     0.1     0.1   205.9   411.9   453.0   480.5   517.1   558.3   594.9   640.6   681.8
   2345.4     0.0     0.1     0.1   187.6   402.7   439.3   471.3   512.5   553.7   590.3   636.1   680.0
    </tableData>
  </table>

  <table name="ITT_N1" type="internal">
    <description> Inter-Turbine Temperature ITT [deg C] depending on N1 and engine run (0=off / 1=running) </description>
    <tableData>
              0     1
        0     0     0
       15   144.1   144.1
       60   258.4   749.5
       96   388.7   980.1
      100   403.6  1083.5
    </tableData>
  </table>

  <table name="CombustionEfficiency_N1" type="internal">
    <description>Dependency of fuel efficiency coefficient on N1 (and RPM)</description>
    <tableData>
      90    0.1221
      91.2  0.2834
      92.2  0.5336
      93.4  0.7188
      94.1  0.7741
      95.2  0.8471
      96.5  0.9001
     100    1
      </tableData>
  </table>
</turboprop_engine>

--- NEW FILE ---
<?xml version="1.0"?>

<!-- Generated by Aero-Matic v 3.3.1

    See: http://wiki.flightgear.org/JSBSim_Thrusters#FGPropeller

    Inputs:
           horsepower: 680
       max engine rpm: 37500
   prop diameter (ft): 8
      prop chord (ft): 0.76
                pitch: variable at 45 inch

    Outputs:
         max prop rpm: 2345.38
           gear ratio: 15.9889
                  Cp0: 0.0803575
                  Ct0: 0.187233
  static thrust (lbs): 2786.61
-->

<propeller version="1.01" name="P7646314-0152">
  <ixx> 25.1034 </ixx>
  <diameter unit="IN"> 94 </diameter>
  <numblades> 4 </numblades>
  <gearratio> 15.9889 </gearratio>
  <cp_factor> 4 </cp_factor>
  <ct_factor> 4 </ct_factor> <!-- set to match the number of blades -->
  <minpitch> 12 </minpitch>
  <maxpitch> 45 </maxpitch>
  <minrpm> 1993.57 </minrpm>
  <maxrpm> 2345.38 </maxrpm>

 <!-- thrust coefficient as a function of advance ratio and blade angle -->
  <table name="C_THRUST" type="internal">
      <tableData>
                       -15         0        15        30        45        60
            0.00    0.0492    0.1132    0.1773    0.2413    0.3054    0.3694
            0.05    0.0431    0.1068    0.1704    0.2337    0.2967    0.3596
            0.10    0.0371    0.1006    0.1638    0.2264    0.2886    0.3503
            0.15    0.0311    0.0946    0.1574    0.2195    0.2808    0.3415
            0.20    0.0253    0.0887    0.1513    0.2129    0.2735    0.3332
            0.25    0.0194    0.0830    0.1454    0.2066    0.2666    0.3254
            0.30    0.0136    0.0774    0.1397    0.2005    0.2600    0.3180
            0.35    0.0079    0.0718    0.1342    0.1948    0.2537    0.3110
            0.40    0.0021    0.0664    0.1288    0.1893    0.2478    0.3044
            0.45   -0.0037    0.0610    0.1236    0.1840    0.2421    0.2981
            0.50   -0.0095    0.0557    0.1185    0.1789    0.2368    0.2922
            0.55   -0.0154    0.0505    0.1136    0.1740    0.2316    0.2866
            0.60   -0.0212    0.0453    0.1088    0.1693    0.2268    0.2813
            0.65   -0.0272    0.0401    0.1041    0.1648    0.2221    0.2762
            0.70   -0.0331    0.0349    0.0994    0.1604    0.2177    0.2715
            0.75   -0.0392    0.0298    0.0949    0.1561    0.2135    0.2670
            0.80   -0.0453    0.0247    0.0904    0.1520    0.2094    0.2627
            0.85   -0.0515    0.0195    0.0860    0.1481    0.2056    0.2586
            0.90   -0.0578    0.0144    0.0817    0.1442    0.2019    0.2548
            0.95   -0.0642    0.0092    0.0774    0.1404    0.1983    0.2511
            1.00   -0.0706    0.0040    0.0731    0.1368    0.1949    0.2476
            1.05   -0.0772   -0.0012    0.0689    0.1332    0.1917    0.2443
            1.10   -0.0839   -0.0065    0.0647    0.1297    0.1885    0.2412
            1.15   -0.0907   -0.0118    0.0605    0.1263    0.1855    0.2382
            1.20   -0.0976   -0.0171    0.0564    0.1230    0.1826    0.2353
            1.25   -0.1047   -0.0225    0.0522    0.1197    0.1798    0.2326
            1.30   -0.1118   -0.0280    0.0481    0.1165    0.1771    0.2300
            1.35   -0.1191   -0.0335    0.0440    0.1133    0.1745    0.2276
            1.40   -0.1265   -0.0391    0.0398    0.1102    0.1720    0.2252
            1.50   -0.1418   -0.0504    0.0315    0.1040    0.1671    0.2208
            1.60   -0.1576   -0.0620    0.0232    0.0981    0.1626    0.2168
            1.70   -0.1739   -0.0739    0.0148    0.0922    0.1583    0.2131
            1.80   -0.1909   -0.0862    0.0062    0.0864    0.1542    0.2097
            1.90   -0.2084   -0.0987   -0.0024    0.0806    0.1502    0.2065
            2.00   -0.2266   -0.1116   -0.0112    0.0749    0.1465    0.2036
            2.10   -0.2454   -0.1249   -0.0201    0.0692    0.1429    0.2009
            2.20   -0.2648   -0.1386   -0.0291    0.0635    0.1393    0.1984
            2.30   -0.2848   -0.1526   -0.0384    0.0578    0.1359    0.1960
            2.40   -0.3055   -0.1670   -0.0478    0.0521    0.1326    0.1938
      </tableData>
  </table>

 <!-- power coefficient as a function of advance ratio and blade angle -->
  <table name="C_POWER" type="internal">
     <tableData>
                       -15         0        15        30        45        60
            0.00    0.0065    0.0313    0.0786    0.1483    0.2405    0.3553
            0.05    0.0076    0.0339    0.0828    0.1541    0.2479    0.3643
            0.10    0.0082    0.0361    0.0866    0.1596    0.2550    0.3730
            0.15    0.0083    0.0379    0.0900    0.1647    0.2619    0.3816
            0.20    0.0080    0.0392    0.0931    0.1695    0.2685    0.3900
            0.25    0.0072    0.0402    0.0957    0.1740    0.2748    0.3983
            0.30    0.0060    0.0407    0.0981    0.1782    0.2810    0.4066
            0.35    0.0043    0.0408    0.1001    0.1821    0.2870    0.4147
            0.40    0.0022    0.0405    0.1017    0.1858    0.2928    0.4227
            0.45   -0.0004    0.0398    0.1031    0.1893    0.2985    0.4308
            0.50   -0.0035    0.0387    0.1041    0.1925    0.3041    0.4388
            0.55   -0.0070    0.0372    0.1047    0.1955    0.3095    0.4468
            0.60   -0.0110    0.0353    0.1051    0.1982    0.3148    0.4547
            0.65   -0.0156    0.0330    0.1051    0.2008    0.3200    0.4627
            0.70   -0.0206    0.0303    0.1048    0.2031    0.3251    0.4708
            0.75   -0.0261    0.0271    0.1042    0.2052    0.3301    0.4788
            0.80   -0.0321    0.0236    0.1033    0.2071    0.3350    0.4869
            0.85   -0.0386    0.0196    0.1021    0.2088    0.3398    0.4951
            0.90   -0.0457    0.0152    0.1005    0.2103    0.3445    0.5033
            0.95   -0.0533    0.0103    0.0986    0.2116    0.3492    0.5115
            1.00   -0.0614    0.0050    0.0964    0.2126    0.3538    0.5198
            1.05   -0.0701   -0.0007    0.0938    0.2135    0.3583    0.5282
            1.10   -0.0794   -0.0069    0.0909    0.2141    0.3627    0.5367
            1.15   -0.0892   -0.0136    0.0877    0.2146    0.3671    0.5452
            1.20   -0.0996   -0.0207    0.0841    0.2148    0.3714    0.5538
            1.25   -0.1106   -0.0282    0.0802    0.2148    0.3756    0.5625
            1.30   -0.1221   -0.0363    0.0759    0.2146    0.3797    0.5712
            1.35   -0.1343   -0.0449    0.0713    0.2142    0.3838    0.5800
            1.40   -0.1471   -0.0539    0.0663    0.2135    0.3877    0.5889
            1.50   -0.1746   -0.0735    0.0553    0.2116    0.3955    0.6070
            1.60   -0.2046   -0.0950    0.0427    0.2087    0.4029    0.6253
            1.70   -0.2372   -0.1187    0.0287    0.2049    0.4100    0.6439
            1.80   -0.2726   -0.1445    0.0130    0.2001    0.4167    0.6628
            1.90   -0.3106   -0.1725   -0.0042    0.1943    0.4230    0.6820
            2.00   -0.3514   -0.2027   -0.0230    0.1875    0.4290    0.7014
            2.10   -0.3950   -0.2351   -0.0435    0.1797    0.4346    0.7211
            2.20   -0.4416   -0.2698   -0.0657    0.1708    0.4397    0.7410
            2.30   -0.4910   -0.3069   -0.0896    0.1609    0.4444    0.7611
            2.40   -0.5434   -0.3463   -0.1152    0.1498    0.4487    0.7815
     </tableData>
  </table>

<!-- thrust effects of helical tip Mach -->
<table name="CT_MACH" type="internal">
  <tableData>
    0.85   1.0
    1.05   0.8
  </tableData>
</table>

<!-- power-required effects of helical tip Mach -->
<table name="CP_MACH" type="internal">
  <tableData>
    0.85   1.0
    1.05   1.8
    2.00   1.4
  </tableData>
</table>

</propeller>