FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 500,000 Max Cl/Cd: 102 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx6617a2-il-500000-n5.txt Download as CSV file: xf-fx6617a2-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-17AII-182 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6647 0.08590 0.08299 -0.0633 1.0000 0.0073
-15.750 -0.6948 0.07634 0.07323 -0.0688 1.0000 0.0072
-15.250 -0.7167 0.06012 0.05658 -0.0834 0.9341 0.0072
-15.000 -0.6539 0.05066 0.04664 -0.1081 0.8842 0.0075
-14.750 -0.6460 0.04722 0.04267 -0.1125 0.7963 0.0076
-14.500 -0.6518 0.04453 0.03971 -0.1128 0.7621 0.0076
-14.250 -0.6548 0.04216 0.03714 -0.1129 0.7375 0.0078
-14.000 -0.6572 0.03984 0.03462 -0.1129 0.7188 0.0078
-13.750 -0.6551 0.03800 0.03263 -0.1127 0.7025 0.0079
-13.500 -0.6516 0.03632 0.03081 -0.1125 0.6888 0.0081
-13.250 -0.6485 0.03460 0.02894 -0.1121 0.6773 0.0082
-13.000 -0.6456 0.03289 0.02710 -0.1116 0.6677 0.0082
-12.750 -0.6396 0.03149 0.02556 -0.1110 0.6588 0.0085
-12.500 -0.6328 0.03014 0.02409 -0.1104 0.6507 0.0086
-12.250 -0.6262 0.02882 0.02264 -0.1096 0.6435 0.0088
-12.000 -0.6187 0.02756 0.02126 -0.1087 0.6365 0.0090
-11.750 -0.6107 0.02639 0.01996 -0.1078 0.6296 0.0092
-11.500 -0.6027 0.02521 0.01867 -0.1067 0.6243 0.0094
-11.250 -0.5943 0.02410 0.01745 -0.1056 0.6186 0.0096
-11.000 -0.5830 0.02329 0.01658 -0.1047 0.6137 0.0099
-10.750 -0.5715 0.02252 0.01574 -0.1036 0.6095 0.0102
-10.500 -0.5599 0.02185 0.01501 -0.1024 0.6053 0.0105
-10.250 -0.5481 0.02131 0.01439 -0.1007 0.6012 0.0109
-10.000 -0.5390 0.02072 0.01371 -0.0985 0.5977 0.0112
-9.750 -0.5240 0.02020 0.01310 -0.0970 0.5944 0.0119
-9.500 -0.5080 0.01962 0.01241 -0.0957 0.5909 0.0124
-9.250 -0.4916 0.01905 0.01179 -0.0945 0.5874 0.0128
-9.000 -0.4723 0.01865 0.01134 -0.0936 0.5839 0.0135
-8.500 -0.4326 0.01779 0.01034 -0.0919 0.5782 0.0149
-8.250 -0.4113 0.01739 0.00986 -0.0912 0.5756 0.0157
-8.000 -0.3911 0.01690 0.00930 -0.0903 0.5729 0.0163
-7.750 -0.3707 0.01642 0.00878 -0.0895 0.5703 0.0171
-7.500 -0.3486 0.01605 0.00836 -0.0889 0.5679 0.0180
-7.250 -0.3262 0.01571 0.00794 -0.0883 0.5656 0.0188
-7.000 -0.3029 0.01538 0.00755 -0.0878 0.5635 0.0196
-6.750 -0.2789 0.01507 0.00720 -0.0874 0.5612 0.0204
-6.500 -0.2570 0.01459 0.00668 -0.0868 0.5588 0.0215
-6.250 -0.2332 0.01426 0.00633 -0.0864 0.5562 0.0226
-6.000 -0.2089 0.01398 0.00599 -0.0860 0.5540 0.0237
-5.750 -0.1842 0.01373 0.00568 -0.0856 0.5519 0.0246
-5.500 -0.1594 0.01349 0.00538 -0.0853 0.5500 0.0255
-5.250 -0.1346 0.01321 0.00506 -0.0850 0.5482 0.0268
-5.000 -0.1089 0.01297 0.00480 -0.0848 0.5464 0.0281
-4.750 -0.0830 0.01276 0.00456 -0.0846 0.5445 0.0295
-4.500 -0.0569 0.01258 0.00435 -0.0844 0.5425 0.0317
-4.250 -0.0311 0.01237 0.00414 -0.0842 0.5403 0.0372
-4.000 -0.0059 0.01211 0.00392 -0.0839 0.5382 0.0533
-3.750 0.0184 0.01177 0.00368 -0.0836 0.5363 0.0884
-3.500 0.0427 0.01143 0.00347 -0.0833 0.5346 0.1341
-3.250 0.0667 0.01105 0.00326 -0.0829 0.5330 0.1916
-3.000 0.0901 0.01055 0.00304 -0.0825 0.5314 0.2713
-2.750 0.1102 0.00978 0.00276 -0.0817 0.5295 0.4035
-2.500 0.1344 0.00951 0.00276 -0.0812 0.5275 0.4861
-2.250 0.1615 0.00950 0.00279 -0.0811 0.5256 0.5168
-2.000 0.1893 0.00954 0.00281 -0.0811 0.5238 0.5347
-1.750 0.2171 0.00960 0.00284 -0.0811 0.5221 0.5475
-1.500 0.2448 0.00966 0.00287 -0.0811 0.5203 0.5568
-1.250 0.2728 0.00975 0.00288 -0.0812 0.5185 0.5657
-1.000 0.3007 0.00979 0.00293 -0.0813 0.5168 0.5720
-0.750 0.3289 0.00983 0.00295 -0.0814 0.5151 0.5774
-0.500 0.3572 0.00987 0.00295 -0.0816 0.5134 0.5805
-0.250 0.3853 0.00989 0.00297 -0.0817 0.5117 0.5833
0.000 0.4132 0.00993 0.00300 -0.0819 0.5100 0.5863
0.250 0.4411 0.00998 0.00303 -0.0820 0.5083 0.5894
0.500 0.4690 0.01003 0.00305 -0.0821 0.5065 0.5926
0.750 0.4968 0.01010 0.00307 -0.0822 0.5047 0.5955
1.000 0.5246 0.01017 0.00309 -0.0824 0.5030 0.5977
1.250 0.5525 0.01020 0.00315 -0.0825 0.5015 0.5997
1.500 0.5803 0.01024 0.00321 -0.0826 0.5000 0.6018
1.750 0.6081 0.01028 0.00327 -0.0828 0.4983 0.6038
2.000 0.6358 0.01033 0.00334 -0.0829 0.4965 0.6060
2.250 0.6635 0.01039 0.00340 -0.0830 0.4947 0.6085
2.500 0.6910 0.01045 0.00345 -0.0831 0.4928 0.6109
2.750 0.7184 0.01053 0.00351 -0.0832 0.4910 0.6130
3.000 0.7456 0.01059 0.00358 -0.0832 0.4893 0.6150
3.250 0.7728 0.01068 0.00368 -0.0833 0.4876 0.6172
3.500 0.7999 0.01073 0.00379 -0.0833 0.4857 0.6195
3.750 0.8270 0.01079 0.00389 -0.0834 0.4837 0.6218
4.000 0.8541 0.01086 0.00399 -0.0834 0.4816 0.6240
4.250 0.8810 0.01093 0.00410 -0.0834 0.4795 0.6261
4.500 0.9078 0.01101 0.00420 -0.0835 0.4776 0.6283
4.750 0.9344 0.01110 0.00431 -0.0834 0.4759 0.6306
5.000 0.9608 0.01119 0.00444 -0.0834 0.4742 0.6334
5.250 0.9872 0.01130 0.00458 -0.0833 0.4726 0.6363
5.500 1.0135 0.01139 0.00475 -0.0833 0.4708 0.6393
5.750 1.0396 0.01147 0.00491 -0.0832 0.4685 0.6419
6.000 1.0649 0.01154 0.00502 -0.0829 0.4646 0.6443
6.250 1.0894 0.01160 0.00511 -0.0825 0.4603 0.6465
6.500 1.1137 0.01169 0.00525 -0.0820 0.4562 0.6488
6.750 1.1383 0.01176 0.00541 -0.0816 0.4517 0.6514
7.000 1.1623 0.01186 0.00556 -0.0812 0.4476 0.6544
7.250 1.1853 0.01198 0.00570 -0.0805 0.4435 0.6576
7.500 1.2091 0.01209 0.00590 -0.0800 0.4385 0.6607
7.750 1.2315 0.01220 0.00608 -0.0792 0.4331 0.6637
8.000 1.2523 0.01234 0.00627 -0.0782 0.4270 0.6668
8.250 1.2730 0.01248 0.00648 -0.0771 0.4187 0.6703
8.500 1.2906 0.01268 0.00670 -0.0755 0.4080 0.6740
8.750 1.2995 0.01296 0.00695 -0.0722 0.3898 0.6776
9.000 1.2983 0.01358 0.00746 -0.0673 0.3604 0.6815
9.250 1.2868 0.01468 0.00836 -0.0610 0.3220 0.6861
9.500 1.2703 0.01615 0.00965 -0.0547 0.2831 0.6912
9.750 1.2525 0.01795 0.01134 -0.0490 0.2515 0.6966
10.000 1.2309 0.02039 0.01368 -0.0440 0.2202 0.7028
10.250 1.2155 0.02297 0.01620 -0.0406 0.1965 0.7094
10.500 1.1905 0.02662 0.01975 -0.0372 0.1646 0.7169
10.750 1.1858 0.02900 0.02216 -0.0356 0.1513 0.7256
11.000 1.1698 0.03237 0.02550 -0.0336 0.1283 0.7362
11.250 1.1560 0.03569 0.02879 -0.0319 0.1072 0.7501
11.750 1.1488 0.04192 0.03522 -0.0321 0.0716 0.8390
12.000 1.1911 0.04773 0.04108 -0.0454 0.0400 0.9990
12.250 1.1919 0.05059 0.04393 -0.0454 0.0322 1.0000
12.500 1.1939 0.05310 0.04645 -0.0450 0.0275 1.0000
12.750 1.1945 0.05581 0.04916 -0.0447 0.0192 1.0000
13.000 1.1955 0.05846 0.05182 -0.0444 0.0162 1.0000
13.250 1.1976 0.06106 0.05442 -0.0442 0.0143 1.0000
13.500 1.2027 0.06336 0.05677 -0.0441 0.0136 1.0000
13.750 1.2067 0.06581 0.05928 -0.0440 0.0130 1.0000
14.000 1.2109 0.06822 0.06175 -0.0439 0.0125 1.0000
14.250 1.2129 0.07093 0.06450 -0.0438 0.0118 1.0000
14.500 1.2162 0.07349 0.06712 -0.0437 0.0114 1.0000
14.750 1.2195 0.07609 0.06979 -0.0437 0.0106 1.0000
15.000 1.2230 0.07869 0.07245 -0.0438 0.0105 1.0000
15.250 1.2270 0.08122 0.07505 -0.0438 0.0101 1.0000
15.500 1.2300 0.08389 0.07779 -0.0439 0.0098 1.0000
15.750 1.2329 0.08660 0.08056 -0.0440 0.0095 1.0000
16.000 1.2356 0.08935 0.08337 -0.0442 0.0091 1.0000
16.250 1.2363 0.09239 0.08648 -0.0445 0.0089 1.0000
16.500 1.2362 0.09551 0.08965 -0.0447 0.0086 1.0000
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Polar data table (+)
Polar graphs
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