EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 642 AIRFOIL (e642-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.4 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e642-il-1000000.txt Download as CSV file: xf-e642-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2978 0.08306 0.08026 -0.0799 0.7198 0.0140
-10.750 -0.3068 0.07716 0.07437 -0.0831 0.7172 0.0140
-10.500 -0.3329 0.06625 0.06349 -0.0915 0.7149 0.0139
-10.250 -0.3750 0.05669 0.05380 -0.0965 0.7122 0.0136
-10.000 -0.4060 0.05133 0.04830 -0.0958 0.7096 0.0135
-9.750 -0.4260 0.04805 0.04492 -0.0933 0.7071 0.0137
-9.500 -0.4478 0.04484 0.04158 -0.0891 0.7045 0.0138
-9.250 -0.4626 0.04201 0.03859 -0.0850 0.7021 0.0140
-8.250 -0.5090 0.02265 0.01713 -0.0655 0.6940 0.0125
-8.000 -0.4885 0.02173 0.01606 -0.0645 0.6923 0.0123
-7.750 -0.4678 0.02056 0.01474 -0.0636 0.6906 0.0123
-7.500 -0.4459 0.01934 0.01337 -0.0628 0.6888 0.0123
-7.250 -0.4223 0.01863 0.01255 -0.0622 0.6869 0.0122
-7.000 -0.3986 0.01748 0.01127 -0.0617 0.6851 0.0122
-6.750 -0.3743 0.01630 0.00998 -0.0613 0.6833 0.0122
-6.500 -0.3497 0.01533 0.00892 -0.0609 0.6816 0.0123
-6.250 -0.3265 0.01426 0.00778 -0.0604 0.6796 0.0126
-6.000 -0.3026 0.01361 0.00711 -0.0599 0.6784 0.0129
-5.750 -0.2785 0.01308 0.00657 -0.0594 0.6771 0.0132
-5.500 -0.2544 0.01259 0.00605 -0.0588 0.6755 0.0135
-5.250 -0.2302 0.01216 0.00559 -0.0583 0.6739 0.0138
-5.000 -0.2056 0.01178 0.00518 -0.0578 0.6723 0.0143
-4.750 -0.1807 0.01145 0.00481 -0.0574 0.6708 0.0148
-4.500 -0.1556 0.01114 0.00447 -0.0570 0.6692 0.0151
-4.250 -0.1297 0.01091 0.00420 -0.0568 0.6676 0.0155
-4.000 -0.1050 0.01057 0.00381 -0.0563 0.6658 0.0160
-3.750 -0.0797 0.01032 0.00352 -0.0560 0.6638 0.0169
-3.500 -0.0535 0.01009 0.00329 -0.0558 0.6626 0.0179
-3.250 -0.0269 0.00991 0.00310 -0.0556 0.6612 0.0194
-3.000 -0.0007 0.00969 0.00289 -0.0554 0.6596 0.0231
-2.750 0.0238 0.00931 0.00269 -0.0550 0.6579 0.0614
-2.500 0.0471 0.00884 0.00252 -0.0544 0.6561 0.1404
-2.250 0.0696 0.00833 0.00237 -0.0538 0.6544 0.2428
-2.000 0.0896 0.00762 0.00221 -0.0529 0.6527 0.3989
-1.750 0.1086 0.00683 0.00202 -0.0517 0.6510 0.5779
-1.500 0.1271 0.00626 0.00216 -0.0500 0.6489 0.7801
-1.250 0.1556 0.00639 0.00230 -0.0500 0.6474 0.8057
-1.000 0.1841 0.00652 0.00241 -0.0501 0.6458 0.8189
-0.750 0.2119 0.00673 0.00264 -0.0499 0.6440 0.8324
-0.500 0.2401 0.00689 0.00279 -0.0498 0.6421 0.8394
-0.250 0.2687 0.00699 0.00285 -0.0500 0.6401 0.8447
0.000 0.2956 0.00717 0.00305 -0.0495 0.6381 0.8506
0.250 0.3236 0.00734 0.00319 -0.0494 0.6360 0.8564
0.500 0.3514 0.00747 0.00329 -0.0494 0.6336 0.8608
0.750 0.3781 0.00758 0.00342 -0.0490 0.6316 0.8643
1.000 0.4052 0.00767 0.00353 -0.0488 0.6294 0.8684
1.250 0.4334 0.00775 0.00361 -0.0489 0.6268 0.8722
1.500 0.4618 0.00776 0.00360 -0.0491 0.6240 0.8747
1.750 0.4892 0.00772 0.00355 -0.0491 0.6213 0.8762
2.000 0.5175 0.00775 0.00354 -0.0494 0.6182 0.8771
2.250 0.5457 0.00772 0.00353 -0.0496 0.6155 0.8779
2.500 0.5741 0.00768 0.00350 -0.0500 0.6122 0.8786
2.750 0.6025 0.00765 0.00348 -0.0503 0.6087 0.8794
3.000 0.6309 0.00763 0.00345 -0.0506 0.6052 0.8801
3.250 0.6595 0.00763 0.00344 -0.0510 0.6014 0.8807
3.500 0.6879 0.00759 0.00343 -0.0513 0.5969 0.8813
3.750 0.7161 0.00757 0.00341 -0.0516 0.5920 0.8821
4.000 0.7442 0.00758 0.00341 -0.0519 0.5873 0.8827
4.250 0.7727 0.00755 0.00342 -0.0523 0.5815 0.8832
4.500 0.8006 0.00755 0.00341 -0.0526 0.5753 0.8837
4.750 0.8288 0.00755 0.00344 -0.0529 0.5685 0.8842
5.000 0.8564 0.00757 0.00345 -0.0532 0.5603 0.8848
5.250 0.8839 0.00761 0.00350 -0.0534 0.5504 0.8854
5.500 0.9106 0.00767 0.00355 -0.0534 0.5384 0.8861
5.750 0.9365 0.00777 0.00361 -0.0534 0.5236 0.8867
6.000 0.9615 0.00792 0.00372 -0.0532 0.5062 0.8872
6.250 0.9854 0.00812 0.00386 -0.0527 0.4877 0.8877
6.500 1.0085 0.00836 0.00403 -0.0522 0.4675 0.8881
6.750 1.0301 0.00866 0.00425 -0.0514 0.4435 0.8886
7.000 1.0483 0.00906 0.00451 -0.0500 0.4116 0.8893
7.250 1.0628 0.00956 0.00483 -0.0480 0.3707 0.8902
7.500 1.0765 0.01007 0.00518 -0.0458 0.3367 0.8911
7.750 1.0918 0.01048 0.00550 -0.0439 0.3113 0.8922
8.000 1.1031 0.01095 0.00586 -0.0412 0.2851 0.8933
8.250 1.1086 0.01148 0.00626 -0.0375 0.2578 0.8945
8.500 1.1146 0.01209 0.00676 -0.0340 0.2325 0.8958
8.750 1.1242 0.01264 0.00724 -0.0313 0.2136 0.8970
9.000 1.1330 0.01324 0.00778 -0.0286 0.1952 0.8982
9.250 1.1397 0.01397 0.00842 -0.0258 0.1766 0.8995
9.500 1.1464 0.01476 0.00915 -0.0232 0.1598 0.9008
9.750 1.1533 0.01562 0.00994 -0.0208 0.1433 0.9020
10.000 1.1593 0.01661 0.01086 -0.0185 0.1265 0.9031
10.250 1.1639 0.01772 0.01189 -0.0162 0.1096 0.9046
10.500 1.1677 0.01893 0.01303 -0.0139 0.0933 0.9065
10.750 1.1730 0.02013 0.01418 -0.0119 0.0788 0.9082
11.000 1.1775 0.02145 0.01544 -0.0100 0.0642 0.9098
11.250 1.1784 0.02304 0.01694 -0.0079 0.0476 0.9115
11.500 1.1783 0.02477 0.01856 -0.0059 0.0320 0.9133
11.750 1.1809 0.02638 0.02012 -0.0042 0.0206 0.9150
12.000 1.1834 0.02806 0.02176 -0.0026 0.0131 0.9166
12.250 1.1911 0.02942 0.02316 -0.0015 0.0111 0.9180
12.500 1.1985 0.03080 0.02457 -0.0004 0.0100 0.9200
12.750 1.2057 0.03222 0.02606 0.0007 0.0094 0.9222
13.000 1.2144 0.03356 0.02747 0.0015 0.0090 0.9243
13.250 1.2221 0.03503 0.02901 0.0024 0.0086 0.9267
13.500 1.2305 0.03648 0.03053 0.0031 0.0084 0.9292
13.750 1.2377 0.03808 0.03220 0.0038 0.0081 0.9318
14.000 1.2439 0.03976 0.03396 0.0045 0.0079 0.9356
14.250 1.2483 0.04163 0.03592 0.0052 0.0076 0.9405
14.500 1.2522 0.04366 0.03805 0.0058 0.0074 0.9469
14.750 1.2584 0.04580 0.04030 0.0058 0.0073 0.9584
15.000 1.2586 0.04935 0.04400 0.0046 0.0070 0.9725
15.250 1.2638 0.05163 0.04635 0.0044 0.0070 1.0000
15.500 1.2696 0.05385 0.04865 0.0042 0.0069 1.0000
15.750 1.2736 0.05633 0.05120 0.0041 0.0068 1.0000
16.000 1.2774 0.05887 0.05382 0.0038 0.0066 1.0000
16.250 1.2794 0.06168 0.05671 0.0035 0.0065 1.0000
16.500 1.2803 0.06468 0.05979 0.0030 0.0064 1.0000
16.750 1.2806 0.06784 0.06303 0.0025 0.0063 1.0000
17.000 1.2793 0.07127 0.06655 0.0018 0.0062 1.0000
17.250 1.2777 0.07481 0.07018 0.0010 0.0061 1.0000
17.500 1.2767 0.07836 0.07381 0.0000 0.0060 1.0000
17.750 1.2723 0.08247 0.07801 -0.0012 0.0059 1.0000
18.000 1.2708 0.08625 0.08188 -0.0024 0.0059 1.0000
18.250 1.2656 0.09061 0.08634 -0.0039 0.0059 1.0000
18.500 1.2617 0.09488 0.09070 -0.0054 0.0058 1.0000
18.750 1.2576 0.09927 0.09517 -0.0071 0.0057 1.0000
19.000 1.2506 0.10417 0.10017 -0.0091 0.0056 1.0000
19.250 1.2475 0.10852 0.10461 -0.0110 0.0056 1.0000
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Polar data table (+)
Polar graphs
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