106 lines
6.1 KiB
XML
106 lines
6.1 KiB
XML
<?xml version="1.0"?>
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<!-- Generated by Aero-Matic v 1.1
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Inputs:
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horsepower: 900
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pitch: variable
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max engine rpm: 2000
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prop diameter (ft): 8.8587
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Outputs:
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max prop rpm: 2118.03
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gear ratio: 0.94
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Cp0: 0.086736
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Ct0: 0.202095
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static thrust (lbs): 3688.16
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-->
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<propeller name="prop">
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<ixx> 17.16 </ixx>
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<diameter unit="IN"> 106.3 </diameter>
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<numblades> 4 </numblades>
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<gearratio> 0.94 </gearratio>
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<p_factor> 8.40 </p_factor>
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<minpitch> 12 </minpitch>
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<maxpitch> 45 </maxpitch>
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<minrpm> 1800 </minrpm>
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<maxrpm> 2118 </maxrpm>
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<!-- thrust coefficient as a function of advance ratio and blade angle -->
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<table name="C_THRUST" type="internal">
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<tableData>
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-10 0 15 25 35 45 55 65 90
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-0.2 -0.0986 0.0556 0.2021 0.2476 0.2728 0.2880 0.2654 0.2274 0.0000
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0.0 -0.1465 0.0000 0.2021 0.2476 0.2728 0.2906 0.2716 0.2274 0.0000
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0.2 -0.1643 -0.0505 0.1744 0.2425 0.2690 0.2906 0.2716 0.2274 0.0000
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0.4 -0.1643 -0.1174 0.1314 0.2401 0.2639 0.2880 0.2716 0.2274 0.0000
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0.6 -0.1643 -0.1643 0.0695 0.2160 0.2526 0.2805 0.2678 0.2274 0.0000
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0.8 -0.1643 -0.1643 0.0038 0.1617 0.2451 0.2704 0.2678 0.2274 0.0000
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1.0 -0.1643 -0.1643 -0.0657 0.0986 0.2350 0.2565 0.2654 0.2274 0.0000
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1.2 -0.1643 -0.1643 -0.1352 0.0303 0.1932 0.2476 0.2654 0.2274 0.0000
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1.4 -0.1643 -0.1643 -0.1643 -0.0443 0.1390 0.2437 0.2603 0.2274 0.0000
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1.6 -0.1643 -0.1643 -0.1643 -0.1124 0.0758 0.2350 0.2552 0.2274 0.0000
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1.8 -0.1643 -0.1643 -0.1643 -0.1643 0.0127 0.2021 0.2476 0.2274 0.0000
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2.0 -0.1643 -0.1643 -0.1643 -0.1643 -0.0505 0.1578 0.2466 0.2274 0.0000
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2.2 -0.1643 -0.1643 -0.1643 -0.1643 -0.1138 0.1138 0.2425 0.2274 0.0000
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2.4 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 0.0606 0.1981 0.2274 0.0000
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2.6 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 0.0077 0.1253 0.2021 0.0000
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2.8 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.0455 0.0821 0.1643 0.0000
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3.0 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.0986 0.0430 0.1263 0.0000
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3.2 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1516 0.0038 0.0885 0.0000
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3.4 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.0354 0.0505 0.0000
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3.6 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.0746 0.0127 0.0000
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3.8 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1138 -0.0253 0.0000
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4.0 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1528 -0.0633 0.0000
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6.0 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 -0.1643 0.0000
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</tableData>
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</table>
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<!-- power coefficient as a function of advance ratio and blade angle -->
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<table name="C_POWER" type="internal">
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<tableData>
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-10 0 15 25 35 45 55 65 90
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-0.2 0.0145 0.0289 0.1012 0.2299 0.3964 0.5638 0.6505 0.7199 0.7199
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0.0 0.0579 0.0145 0.0867 0.2142 0.3790 0.5638 0.6531 0.7199 0.7199
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0.2 0.0824 0.0232 0.0839 0.1995 0.3626 0.5638 0.6531 0.7199 0.7199
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0.4 0.1110 0.0506 0.0723 0.1839 0.3443 0.5638 0.6531 0.7199 0.7199
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0.6 0.1362 0.0766 0.0477 0.1709 0.3227 0.5525 0.6505 0.7199 0.7199
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0.8 0.1605 0.1026 0.0145 0.1448 0.3036 0.5274 0.6505 0.7199 0.7199
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1.0 0.1847 0.1275 0.0145 0.1015 0.2862 0.5005 0.6479 0.7199 0.7199
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1.2 0.2099 0.1019 -0.0477 0.0390 0.2533 0.4797 0.6436 0.7199 0.7199
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1.4 0.2342 0.1761 -0.0720 -0.0289 0.1952 0.4727 0.6358 0.7199 0.7199
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1.6 0.2585 0.2012 -0.0841 -0.0867 0.1232 0.4597 0.6219 0.6939 0.7199
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1.8 0.2836 0.2255 -0.0867 -0.1448 0.0362 0.4077 0.6028 0.6791 0.7199
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2.0 0.3079 0.2498 -0.1110 -0.2021 -0.0434 0.3469 0.5742 0.6653 0.7199
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2.2 0.3322 0.2750 -0.1362 -0.2602 -0.1301 0.2819 0.5568 0.6358 0.7199
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2.4 0.3574 0.2992 -0.1605 -0.3183 -0.2168 0.2012 0.5404 0.6219 0.7199
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2.6 0.3816 0.3235 -0.1847 -0.3756 -0.2750 0.0841 0.5274 0.6002 0.7199
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2.8 0.4059 0.3487 -0.2099 -0.4337 -0.3296 -0.0286 0.5161 0.5924 0.7199
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3.0 0.4311 0.3730 -0.2342 -0.4918 -0.3903 -0.1301 0.4987 0.5924 0.7199
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3.2 0.4554 0.3973 -0.2585 -0.5490 -0.4484 -0.2316 0.4666 0.5785 0.7199
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3.4 0.4797 0.4224 -0.2836 -0.6072 -0.5057 -0.3322 0.3617 0.5638 0.7199
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3.6 0.5048 0.4467 -0.3079 -0.6653 -0.5638 -0.4337 0.2541 0.5490 0.7199
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3.8 0.5291 0.4710 -0.3322 -0.7199 -0.6219 -0.5352 0.1414 0.5317 0.7199
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4.0 0.5534 0.4961 -0.3574 -0.7199 -0.7199 -0.6358 0.0286 0.4918 0.7199
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6.0 0.7199 0.7199 -0.7199 -0.7199 -0.7199 -0.7199 -0.7199 -0.4337 0.7199
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</tableData>
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</table>
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<!-- thrust effects of helical tip Mach -->
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<table name="CT_MACH" type="internal">
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<tableData>
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0.85 1.0
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1.05 0.8
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</tableData>
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</table>
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<!-- power-required effects of helical tip Mach -->
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<table name="CP_MACH" type="internal">
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<tableData>
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0.85 1.0
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1.05 1.8
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2.00 1.4
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</tableData>
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</table>
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</propeller> |