FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 100,000 Max Cl/Cd: 5.9 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx6617a2-il-100000.txt Download as CSV file: xf-fx6617a2-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2674 0.13424 0.12984 -0.0497 1.0000 0.1079
-12.500 -0.2913 0.13183 0.12759 -0.0544 1.0000 0.1125
-12.250 -0.2894 0.12737 0.12326 -0.0553 1.0000 0.1143
-12.000 -0.2682 0.12493 0.12096 -0.0531 1.0000 0.1174
-11.750 -0.2586 0.11928 0.11531 -0.0634 0.9516 0.1269
-11.500 -0.2147 0.11304 0.10893 -0.0690 0.9268 0.1334
-11.250 -0.2345 0.10747 0.10333 -0.0827 0.9090 0.1429
-11.000 -0.1649 0.10200 0.09756 -0.0840 0.8854 0.1502
-10.750 -0.1749 0.09684 0.09232 -0.0913 0.8678 0.1597
-10.500 -0.1434 0.09365 0.08892 -0.0919 0.8501 0.1642
-10.250 -0.1633 0.08947 0.08476 -0.0964 0.8372 0.1744
-10.000 -0.1351 0.08682 0.08198 -0.0956 0.8247 0.1789
-9.750 -0.1428 0.08313 0.07828 -0.0980 0.8158 0.1903
-9.500 -0.3380 0.05592 0.05061 -0.1166 0.8128 0.0814
-9.250 -0.3859 0.05244 0.04622 -0.1126 0.8044 0.0714
-9.000 -0.3757 0.04859 0.04222 -0.1120 0.7967 0.0701
-8.750 -0.3687 0.04513 0.03851 -0.1110 0.7899 0.0687
-8.500 -0.3614 0.04217 0.03520 -0.1096 0.7837 0.0674
-8.250 -0.3523 0.03950 0.03216 -0.1080 0.7771 0.0666
-8.000 -0.3386 0.03723 0.02944 -0.1066 0.7718 0.0672
-7.750 -0.3242 0.03564 0.02746 -0.1051 0.7654 0.0693
-7.500 -0.3068 0.03441 0.02577 -0.1036 0.7597 0.0710
-7.250 -0.2825 0.03178 0.02305 -0.1034 0.7555 0.0740
-7.000 -0.2611 0.03071 0.02195 -0.1028 0.7502 0.0779
-6.750 -0.2367 0.02953 0.02060 -0.1022 0.7453 0.0809
-6.500 -0.2115 0.02858 0.01943 -0.1015 0.7412 0.0849
-6.250 -0.1874 0.02740 0.01841 -0.1010 0.7371 0.0902
-6.000 -0.1663 0.02674 0.01777 -0.0998 0.7320 0.0953
-5.750 -0.1467 0.02598 0.01706 -0.0984 0.7277 0.1017
-5.500 -0.1283 0.02535 0.01646 -0.0969 0.7243 0.1143
-5.250 -0.1168 0.02465 0.01600 -0.0948 0.7206 0.1385
-5.000 -0.1236 0.02256 0.01514 -0.0911 0.7166 0.2993
-4.750 -0.1139 0.02338 0.01690 -0.0865 0.7128 0.5358
-4.500 -0.0888 0.02464 0.01798 -0.0845 0.7094 0.5734
-4.250 -0.0655 0.02608 0.01933 -0.0819 0.7060 0.6022
-4.000 -0.0500 0.02771 0.02099 -0.0784 0.7015 0.6300
-3.750 -0.0292 0.02946 0.02279 -0.0741 0.6980 0.6531
-3.500 -0.0087 0.03032 0.02355 -0.0712 0.6949 0.6744
-3.250 0.0140 0.03074 0.02382 -0.0692 0.6923 0.6922
-3.000 0.0289 0.03147 0.02455 -0.0662 0.6884 0.7031
-2.750 0.0392 0.03195 0.02501 -0.0638 0.6841 0.7136
-2.500 0.0538 0.03213 0.02506 -0.0627 0.6808 0.7244
-2.250 0.0762 0.03224 0.02508 -0.0615 0.6782 0.7314
-2.000 0.1011 0.03211 0.02476 -0.0613 0.6759 0.7412
-1.750 0.0957 0.03327 0.02602 -0.0575 0.6706 0.7482
-1.500 0.0987 0.03404 0.02676 -0.0553 0.6664 0.7568
-1.250 0.1135 0.03446 0.02714 -0.0536 0.6636 0.7643
-1.000 0.1374 0.03451 0.02705 -0.0536 0.6613 0.7724
-0.750 0.1683 0.03436 0.02677 -0.0537 0.6596 0.7785
-0.500 0.0718 0.03920 0.03192 -0.0422 0.6510 0.7840
-0.250 0.0677 0.04048 0.03318 -0.0397 0.6483 0.7894
0.000 0.1020 0.04038 0.03296 -0.0405 0.6459 0.7948
0.250 0.1619 0.03954 0.03193 -0.0443 0.6442 0.8013
0.500 0.0921 0.04374 0.03626 -0.0359 0.6414 0.8060
0.750 0.0794 0.04571 0.03824 -0.0332 0.6400 0.8114
1.000 0.0812 0.04730 0.03978 -0.0322 0.6400 0.8169
1.250 0.0910 0.04865 0.04110 -0.0316 0.6413 0.8216
1.500 0.1046 0.04999 0.04240 -0.0314 0.6423 0.8264
1.750 0.1261 0.05130 0.04365 -0.0322 0.6440 0.8314
2.000 0.0203 0.05663 0.04925 -0.0255 0.6979 0.8361
2.250 0.0516 0.05778 0.05032 -0.0268 0.6937 0.8409
2.500 0.0912 0.05977 0.05223 -0.0294 0.6915 0.8463
2.750 0.0791 0.05953 0.05198 -0.0262 0.6808 0.8514
3.000 0.1115 0.06093 0.05332 -0.0280 0.6775 0.8565
3.250 0.1524 0.06313 0.05546 -0.0309 0.6755 0.8626
3.500 0.1422 0.06286 0.05519 -0.0282 0.6639 0.8685
3.750 0.1788 0.06457 0.05687 -0.0306 0.6609 0.8752
4.000 0.1785 0.06540 0.05772 -0.0295 0.6533 0.8821
4.250 0.2074 0.06665 0.05898 -0.0313 0.6475 0.8907
4.500 0.2485 0.06862 0.06098 -0.0345 0.6448 0.9007
4.750 0.2502 0.06955 0.06199 -0.0347 0.6356 0.9122
5.000 0.2944 0.07150 0.06402 -0.0396 0.6308 0.9281
5.250 0.3433 0.07403 0.06660 -0.0445 0.6284 1.0000
5.500 0.3307 0.07458 0.06713 -0.0428 0.6178 1.0000
5.750 0.3649 0.07652 0.06904 -0.0451 0.6141 1.0000
6.000 0.4077 0.07931 0.07179 -0.0483 0.6123 1.0000
6.250 0.3905 0.07961 0.07209 -0.0462 0.6007 1.0000
6.500 0.4257 0.08182 0.07428 -0.0485 0.5978 1.0000
6.750 0.4199 0.08321 0.07567 -0.0477 0.5891 1.0000
7.000 0.4482 0.08496 0.07740 -0.0492 0.5837 1.0000
7.250 0.4859 0.08754 0.07998 -0.0515 0.5813 1.0000
7.500 0.4713 0.08860 0.08104 -0.0499 0.5709 1.0000
7.750 0.5042 0.09065 0.08309 -0.0515 0.5668 1.0000
8.000 0.5464 0.09376 0.08621 -0.0539 0.5649 1.0000
8.250 0.5233 0.09426 0.08672 -0.0517 0.5528 1.0000
8.500 0.5623 0.09682 0.08931 -0.0535 0.5499 1.0000
8.750 0.5446 0.09824 0.09075 -0.0521 0.5396 1.0000
9.000 0.5786 0.10034 0.09287 -0.0534 0.5352 1.0000
9.250 0.5698 0.10242 0.09498 -0.0527 0.5269 1.0000
9.500 0.5970 0.10423 0.09684 -0.0535 0.5207 1.0000
9.750 0.6296 0.10720 0.09987 -0.0548 0.5176 1.0000
10.000 0.6195 0.10830 0.10100 -0.0539 0.5059 1.0000
10.250 0.6558 0.11112 0.10389 -0.0551 0.5024 1.0000
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Polar data table (+)
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