EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 642 AIRFOIL (e642-il) Reynolds number: 500,000 Max Cl/Cd: 92.6 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e642-il-500000-n5.txt Download as CSV file: xf-e642-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 642 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4971 0.04891 0.04497 -0.0955 0.7255 0.0086
-11.250 -0.5185 0.04497 0.04084 -0.0950 0.7218 0.0087
-10.750 -0.5557 0.03869 0.03410 -0.0901 0.7145 0.0087
-10.500 -0.5654 0.03655 0.03174 -0.0869 0.7115 0.0087
-10.250 -0.5769 0.03424 0.02919 -0.0828 0.7087 0.0087
-10.000 -0.5868 0.03200 0.02670 -0.0785 0.7060 0.0088
-9.750 -0.5866 0.02980 0.02423 -0.0754 0.7034 0.0088
-9.500 -0.5791 0.02811 0.02234 -0.0732 0.7009 0.0089
-9.250 -0.5675 0.02674 0.02079 -0.0713 0.6985 0.0091
-9.000 -0.5527 0.02571 0.01963 -0.0699 0.6964 0.0093
-8.500 -0.5188 0.02358 0.01717 -0.0674 0.6924 0.0096
-8.250 -0.4998 0.02250 0.01592 -0.0663 0.6901 0.0097
-8.000 -0.4796 0.02144 0.01471 -0.0654 0.6879 0.0099
-7.750 -0.4585 0.02039 0.01349 -0.0646 0.6860 0.0100
-7.500 -0.4363 0.01947 0.01242 -0.0638 0.6841 0.0101
-7.250 -0.4135 0.01863 0.01144 -0.0632 0.6824 0.0103
-7.000 -0.3903 0.01787 0.01056 -0.0626 0.6808 0.0105
-6.750 -0.3669 0.01717 0.00974 -0.0620 0.6792 0.0107
-6.500 -0.3432 0.01655 0.00905 -0.0615 0.6777 0.0109
-6.250 -0.3193 0.01599 0.00841 -0.0610 0.6762 0.0112
-6.000 -0.2955 0.01547 0.00783 -0.0604 0.6744 0.0114
-5.750 -0.2715 0.01501 0.00733 -0.0599 0.6725 0.0116
-5.500 -0.2478 0.01455 0.00682 -0.0593 0.6708 0.0118
-5.250 -0.2252 0.01397 0.00620 -0.0586 0.6692 0.0122
-5.000 -0.2017 0.01354 0.00574 -0.0580 0.6677 0.0125
-4.750 -0.1773 0.01321 0.00538 -0.0576 0.6662 0.0130
-4.500 -0.1524 0.01293 0.00507 -0.0572 0.6647 0.0138
-4.250 -0.1274 0.01267 0.00475 -0.0568 0.6631 0.0144
-4.000 -0.1020 0.01241 0.00447 -0.0565 0.6616 0.0150
-3.750 -0.0765 0.01217 0.00421 -0.0562 0.6601 0.0155
-3.500 -0.0511 0.01191 0.00393 -0.0559 0.6584 0.0167
-3.250 -0.0253 0.01171 0.00371 -0.0556 0.6567 0.0182
-3.000 0.0008 0.01153 0.00352 -0.0554 0.6549 0.0206
-2.750 0.0257 0.01124 0.00333 -0.0551 0.6531 0.0400
-2.500 0.0492 0.01085 0.00315 -0.0546 0.6514 0.0959
-2.250 0.0726 0.01045 0.00301 -0.0540 0.6498 0.1638
-2.000 0.0963 0.01011 0.00288 -0.0536 0.6481 0.2348
-1.750 0.1167 0.00949 0.00273 -0.0527 0.6464 0.3655
-1.500 0.1352 0.00875 0.00257 -0.0515 0.6445 0.5198
-1.250 0.1471 0.00806 0.00292 -0.0480 0.6425 0.7717
-1.000 0.1743 0.00828 0.00311 -0.0477 0.6404 0.8130
-0.750 0.2018 0.00845 0.00326 -0.0475 0.6384 0.8232
-0.500 0.2287 0.00866 0.00344 -0.0471 0.6365 0.8340
-0.250 0.2561 0.00883 0.00355 -0.0469 0.6346 0.8439
0.000 0.2825 0.00903 0.00375 -0.0463 0.6327 0.8493
0.250 0.3095 0.00917 0.00387 -0.0461 0.6307 0.8554
0.500 0.3368 0.00924 0.00393 -0.0460 0.6284 0.8603
0.750 0.3637 0.00930 0.00400 -0.0458 0.6258 0.8627
1.000 0.3914 0.00932 0.00400 -0.0458 0.6232 0.8643
1.250 0.4195 0.00932 0.00398 -0.0461 0.6206 0.8656
1.500 0.4479 0.00933 0.00394 -0.0464 0.6181 0.8666
1.750 0.4762 0.00933 0.00393 -0.0467 0.6154 0.8677
2.000 0.5043 0.00932 0.00394 -0.0469 0.6120 0.8688
2.250 0.5325 0.00930 0.00392 -0.0473 0.6084 0.8696
2.500 0.5608 0.00929 0.00390 -0.0476 0.6048 0.8706
2.750 0.5891 0.00930 0.00387 -0.0479 0.6013 0.8716
3.000 0.6172 0.00928 0.00390 -0.0483 0.5966 0.8723
3.250 0.6454 0.00928 0.00390 -0.0486 0.5918 0.8729
3.500 0.6734 0.00928 0.00388 -0.0489 0.5873 0.8736
3.750 0.7015 0.00929 0.00392 -0.0492 0.5816 0.8742
4.000 0.7284 0.00928 0.00393 -0.0492 0.5752 0.8748
4.250 0.7553 0.00930 0.00397 -0.0493 0.5682 0.8755
4.500 0.7818 0.00931 0.00399 -0.0492 0.5593 0.8760
4.750 0.8083 0.00934 0.00403 -0.0492 0.5490 0.8765
5.000 0.8341 0.00940 0.00409 -0.0491 0.5378 0.8771
5.250 0.8591 0.00949 0.00416 -0.0487 0.5239 0.8777
5.500 0.8831 0.00961 0.00425 -0.0483 0.5082 0.8783
5.750 0.9060 0.00979 0.00438 -0.0476 0.4906 0.8790
6.000 0.9279 0.01002 0.00456 -0.0468 0.4722 0.8797
6.250 0.9485 0.01029 0.00477 -0.0458 0.4522 0.8806
6.500 0.9687 0.01058 0.00501 -0.0447 0.4324 0.8817
6.750 0.9875 0.01091 0.00528 -0.0434 0.4120 0.8827
7.000 1.0050 0.01128 0.00558 -0.0419 0.3903 0.8837
7.250 1.0211 0.01168 0.00591 -0.0402 0.3685 0.8847
7.500 1.0338 0.01213 0.00628 -0.0378 0.3453 0.8858
7.750 1.0388 0.01270 0.00672 -0.0341 0.3160 0.8872
8.000 1.0431 0.01342 0.00731 -0.0306 0.2863 0.8885
8.250 1.0459 0.01424 0.00798 -0.0269 0.2567 0.8899
8.500 1.0477 0.01514 0.00876 -0.0234 0.2281 0.8914
8.750 1.0521 0.01604 0.00957 -0.0204 0.2047 0.8928
9.000 1.0591 0.01692 0.01040 -0.0181 0.1880 0.8943
9.250 1.0663 0.01787 0.01130 -0.0160 0.1719 0.8960
9.500 1.0731 0.01891 0.01230 -0.0140 0.1545 0.8978
9.750 1.0806 0.02000 0.01334 -0.0122 0.1387 0.8993
10.000 1.0873 0.02119 0.01447 -0.0105 0.1222 0.9008
10.250 1.0923 0.02254 0.01573 -0.0088 0.1044 0.9023
10.500 1.0993 0.02382 0.01695 -0.0073 0.0895 0.9037
10.750 1.1060 0.02509 0.01818 -0.0058 0.0763 0.9052
11.000 1.1123 0.02642 0.01949 -0.0044 0.0638 0.9067
11.250 1.1163 0.02795 0.02095 -0.0029 0.0498 0.9084
11.500 1.1229 0.02934 0.02233 -0.0016 0.0404 0.9101
11.750 1.1276 0.03091 0.02387 -0.0004 0.0307 0.9120
12.000 1.1343 0.03238 0.02534 0.0007 0.0240 0.9139
12.250 1.1390 0.03406 0.02700 0.0018 0.0158 0.9158
12.500 1.1441 0.03575 0.02871 0.0027 0.0117 0.9178
12.750 1.1510 0.03732 0.03032 0.0036 0.0101 0.9198
13.000 1.1581 0.03892 0.03199 0.0043 0.0093 0.9223
13.250 1.1669 0.04040 0.03355 0.0049 0.0088 0.9252
13.500 1.1744 0.04203 0.03527 0.0055 0.0083 0.9287
14.000 1.1866 0.04576 0.03917 0.0064 0.0074 0.9372
14.250 1.1929 0.04781 0.04132 0.0065 0.0072 0.9428
14.500 1.2005 0.04991 0.04353 0.0063 0.0071 0.9500
15.000 1.2147 0.05459 0.04843 0.0050 0.0067 1.0000
15.250 1.2189 0.05703 0.05096 0.0048 0.0067 1.0000
15.500 1.2223 0.05962 0.05364 0.0046 0.0065 1.0000
15.750 1.2246 0.06239 0.05651 0.0043 0.0063 1.0000
16.000 1.2268 0.06527 0.05948 0.0039 0.0062 1.0000
16.250 1.2273 0.06841 0.06272 0.0033 0.0061 1.0000
16.500 1.2277 0.07163 0.06605 0.0026 0.0060 1.0000
16.750 1.2272 0.07505 0.06956 0.0018 0.0059 1.0000
17.000 1.2250 0.07878 0.07339 0.0008 0.0058 1.0000
17.250 1.2237 0.08247 0.07719 -0.0003 0.0058 1.0000
17.500 1.2204 0.08653 0.08134 -0.0015 0.0057 1.0000
17.750 1.2171 0.09064 0.08557 -0.0029 0.0057 1.0000
18.000 1.2128 0.09501 0.09003 -0.0045 0.0056 1.0000
18.250 1.2073 0.09965 0.09477 -0.0063 0.0054 1.0000
18.500 1.2036 0.10409 0.09931 -0.0082 0.0054 1.0000
18.750 1.1976 0.10893 0.10426 -0.0103 0.0054 1.0000
19.000 1.1923 0.11372 0.10916 -0.0124 0.0053 1.0000
19.250 1.1865 0.11867 0.11421 -0.0147 0.0053 1.0000
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Polar data table (+)
Polar graphs
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