Menu
▾
▴
[Jsbsim-cvslogs] CVS: JSBSim/aircraft/pc7/Engines PT6A.xml, NONE, 1.1 Propeller.xml, NONE, 1.1
|
From: Erik H. <eh...@us...> - 2016-06-06 10:49:24
|
Update of /cvsroot/jsbsim/JSBSim/aircraft/pc7/Engines In directory sfp-cvs-1.v30.ch3.sourceforge.com:/tmp/cvs-serv27159/Engines Added Files: PT6A.xml Propeller.xml Log Message: Update to the latest Aeromatic output --- NEW FILE --- <?xml version="1.0"?> <!-- File: PT6A.xml Author: AeromatiC++ v 3.2.5 See: http://wiki.flightgear.org/JSBSim_Engines#FGTurboprop Inputs: name: PT6A type: Turboprop Engine power: 549.8 hp inlet temperature: 725.0 degrees C overall pressure ratio: 6.3:1 Outputs: psfc: 0.641 lbs/hr/hp engine weight: 298.2 lbs engine length: 4.6 ft engine diameter: 1.8 ft --> <turboprop_engine name="PT6A"> <milthrust unit="LBS"> 1231.6 </milthrust> <idlen1> 60.0 </idlen1> <maxn1> 100.0 </maxn1> <maxpower unit="HP"> 549.8 </maxpower> <psfc unit="LBS/HR/HP"> 0.641 </psfc> <n1idle_max_delay> 1 </n1idle_max_delay> <maxstartingtime> 20 </maxstartingtime> <startern1> 20 </startern1> <ielumaxtorque unit="FT*LB"> 1303.7 </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 50 100 150 200 250 503 0.357 0.380 0.400 0.425 0.457 0.486 1048 0.586 0.589 0.600 0.621 0.650 0.686 1328 0.707 0.721 0.731 0.757 0.786 0.821 1496 0.779 0.786 0.808 0.821 0.857 0.900 1684 0.850 0.857 0.874 0.900 0.943 0.979 1896 0.914 0.929 0.946 0.971 1 1.057 2135 1 1.011 1.029 1.043 1.083 1.150 2213 1.029 1.043 1.057 1.079 1.114 1.171 </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 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 862.7 0.0 0.4 25.9 148.0 259.0 281.2 310.8 340.4 370.0 392.2 429.2 458.8 1291.7 0.0 0.4 22.2 170.2 296.0 318.2 347.8 373.7 407.0 436.6 473.6 503.2 1723.0 0.0 0.4 3.7 177.6 325.6 351.5 377.4 407.0 440.3 466.2 503.2 532.8 2154.4 0.0 0.1 0.1 166.5 333.0 366.3 388.5 418.1 451.4 481.0 518.0 551.3 2370.1 0.0 0.1 0.1 151.7 325.6 355.2 381.1 414.4 447.7 477.3 514.3 549.8 </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 15 105.1 105.1 60 188.5 546.7 96 283.5 714.8 100 294.4 790.2 </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 3.2.5 See: http://wiki.flightgear.org/JSBSim_Thrusters#FGPropeller Inputs: horsepower: 549.81 max engine rpm: 37500 prop diameter (ft): 7.91667 prop chord (ft): 0.756031 pitch: variable at 45 inch Outputs: max prop rpm: 2370.06 gear ratio: 15.8224 Cp0: 0.0663477 Ct0: 0.15459 static thrust (lbs): 2253.1 --> <propeller version="1.01" name="prop"> <ixx> 6.01793 </ixx> <diameter unit="IN"> 95 </diameter> <numblades> 4 </numblades> <gearratio> 15.8224 </gearratio> <cp_factor> 1.00 </cp_factor> <ct_factor> 1.00 </ct_factor> <minpitch> 12 </minpitch> <maxpitch> 45 </maxpitch> <minrpm> 2014.55 </minrpm> <maxrpm> 2370.06 </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 0.0499 0.1140 0.1781 0.2421 0.3062 0.3702 0.05 0.0438 0.1076 0.1712 0.2345 0.2975 0.3604 0.10 0.0378 0.1014 0.1645 0.2272 0.2894 0.3511 0.15 0.0319 0.0954 0.1582 0.2202 0.2816 0.3423 0.20 0.0260 0.0895 0.1520 0.2136 0.2743 0.3340 0.25 0.0202 0.0838 0.1461 0.2073 0.2673 0.3261 0.30 0.0144 0.0781 0.1404 0.2013 0.2607 0.3187 0.35 0.0086 0.0726 0.1349 0.1955 0.2544 0.3117 0.40 0.0029 0.0672 0.1296 0.1900 0.2485 0.3051 0.45 -0.0029 0.0618 0.1244 0.1847 0.2428 0.2988 0.50 -0.0087 0.0565 0.1193 0.1796 0.2375 0.2929 0.55 -0.0146 0.0513 0.1144 0.1747 0.2323 0.2872 0.60 -0.0204 0.0461 0.1095 0.1700 0.2275 0.2819 0.65 -0.0263 0.0409 0.1048 0.1655 0.2228 0.2769 0.70 -0.0323 0.0357 0.1002 0.1611 0.2184 0.2721 0.75 -0.0383 0.0306 0.0957 0.1569 0.2142 0.2676 0.80 -0.0444 0.0255 0.0912 0.1528 0.2101 0.2633 0.85 -0.0506 0.0203 0.0868 0.1488 0.2063 0.2593 0.90 -0.0569 0.0152 0.0825 0.1449 0.2026 0.2554 0.95 -0.0633 0.0100 0.0782 0.1412 0.1990 0.2517 1.00 -0.0697 0.0049 0.0739 0.1375 0.1956 0.2482 1.05 -0.0763 -0.0004 0.0697 0.1340 0.1924 0.2449 1.10 -0.0830 -0.0056 0.0655 0.1305 0.1892 0.2418 1.15 -0.0897 -0.0109 0.0614 0.1271 0.1862 0.2388 1.20 -0.0966 -0.0162 0.0572 0.1237 0.1833 0.2359 1.25 -0.1036 -0.0216 0.0531 0.1205 0.1805 0.2332 1.30 -0.1108 -0.0270 0.0490 0.1173 0.1778 0.2306 1.35 -0.1180 -0.0325 0.0449 0.1141 0.1752 0.2282 1.40 -0.1254 -0.0381 0.0407 0.1110 0.1727 0.2258 1.50 -0.1406 -0.0494 0.0325 0.1049 0.1679 0.2214 1.60 -0.1564 -0.0609 0.0242 0.0989 0.1633 0.2174 1.70 -0.1727 -0.0728 0.0158 0.0930 0.1590 0.2137 1.80 -0.1896 -0.0850 0.0073 0.0873 0.1549 0.2103 1.90 -0.2071 -0.0975 -0.0013 0.0815 0.1510 0.2071 2.00 -0.2251 -0.1104 -0.0100 0.0759 0.1473 0.2042 2.10 -0.2439 -0.1236 -0.0189 0.0702 0.1437 0.2015 2.20 -0.2632 -0.1371 -0.0279 0.0645 0.1402 0.1990 2.30 -0.2831 -0.1511 -0.0371 0.0589 0.1368 0.1967 2.40 -0.3037 -0.1654 -0.0464 0.0532 0.1335 0.1945 </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 0.0067 0.0317 0.0792 0.1492 0.2418 0.3568 0.05 0.0077 0.0344 0.0835 0.1551 0.2492 0.3658 0.10 0.0084 0.0366 0.0873 0.1605 0.2563 0.3745 0.15 0.0085 0.0384 0.0907 0.1657 0.2631 0.3832 0.20 0.0083 0.0397 0.0938 0.1705 0.2698 0.3916 0.25 0.0075 0.0407 0.0965 0.1750 0.2762 0.3999 0.30 0.0063 0.0412 0.0989 0.1793 0.2824 0.4082 0.35 0.0047 0.0414 0.1009 0.1832 0.2884 0.4163 0.40 0.0025 0.0411 0.1026 0.1870 0.2942 0.4244 0.45 -0.0000 0.0404 0.1039 0.1904 0.3000 0.4325 0.50 -0.0031 0.0394 0.1050 0.1937 0.3055 0.4405 0.55 -0.0066 0.0379 0.1057 0.1967 0.3110 0.4485 0.60 -0.0106 0.0360 0.1061 0.1995 0.3163 0.4565 0.65 -0.0151 0.0337 0.1061 0.2021 0.3215 0.4646 0.70 -0.0201 0.0310 0.1059 0.2044 0.3267 0.4726 0.75 -0.0256 0.0279 0.1053 0.2066 0.3317 0.4807 0.80 -0.0315 0.0244 0.1044 0.2085 0.3366 0.4889 0.85 -0.0380 0.0204 0.1032 0.2102 0.3415 0.4971 0.90 -0.0451 0.0161 0.1017 0.2117 0.3463 0.5053 0.95 -0.0526 0.0112 0.0998 0.2131 0.3510 0.5136 1.00 -0.0607 0.0060 0.0976 0.2142 0.3556 0.5220 1.05 -0.0694 0.0003 0.0951 0.2151 0.3602 0.5304 1.10 -0.0786 -0.0059 0.0923 0.2158 0.3647 0.5389 1.15 -0.0884 -0.0125 0.0891 0.2162 0.3691 0.5475 1.20 -0.0987 -0.0195 0.0855 0.2165 0.3734 0.5562 1.25 -0.1097 -0.0271 0.0817 0.2166 0.3777 0.5649 1.30 -0.1212 -0.0351 0.0775 0.2164 0.3818 0.5737 1.35 -0.1334 -0.0436 0.0729 0.2161 0.3860 0.5826 1.40 -0.1461 -0.0526 0.0680 0.2155 0.3900 0.5915 1.50 -0.1735 -0.0720 0.0570 0.2136 0.3979 0.6097 1.60 -0.2034 -0.0935 0.0446 0.2109 0.4054 0.6281 1.70 -0.2359 -0.1171 0.0306 0.2072 0.4126 0.6469 1.80 -0.2711 -0.1428 0.0151 0.2025 0.4195 0.6660 1.90 -0.3090 -0.1706 -0.0019 0.1969 0.4260 0.6853 2.00 -0.3497 -0.2006 -0.0206 0.1903 0.4321 0.7049 2.10 -0.3932 -0.2329 -0.0410 0.1826 0.4379 0.7248 2.20 -0.4396 -0.2675 -0.0630 0.1739 0.4432 0.7449 2.30 -0.4889 -0.3044 -0.0867 0.1641 0.4481 0.7652 2.40 -0.5412 -0.3436 -0.1122 0.1532 0.4525 0.7858 </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> |
