EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 682 AIRFOIL (e682-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.73 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e682-il-1000000.txt Download as CSV file: xf-e682-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 682 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1973 0.08560 0.08311 -0.0842 0.7837 0.0141
-11.500 -0.2007 0.08062 0.07814 -0.0864 0.7830 0.0143
-11.250 -0.2073 0.07497 0.07250 -0.0888 0.7822 0.0144
-11.000 -0.2179 0.06841 0.06595 -0.0918 0.7814 0.0145
-10.750 -0.2394 0.05907 0.05662 -0.0967 0.7807 0.0145
-10.500 -0.3283 0.03928 0.03662 -0.1082 0.7799 0.0140
-10.250 -0.3590 0.03455 0.03174 -0.1073 0.7786 0.0140
-10.000 -0.3834 0.03104 0.02808 -0.1049 0.7771 0.0140
-9.750 -0.4005 0.02859 0.02550 -0.1019 0.7755 0.0141
-9.500 -0.4124 0.02675 0.02355 -0.0983 0.7742 0.0143
-9.250 -0.4238 0.02481 0.02150 -0.0942 0.7731 0.0144
-9.000 -0.4296 0.02229 0.01881 -0.0908 0.7721 0.0146
-8.750 -0.4295 0.02002 0.01636 -0.0880 0.7710 0.0150
-8.500 -0.4265 0.01777 0.01386 -0.0851 0.7698 0.0159
-8.250 -0.4138 0.01812 0.01391 -0.0824 0.7684 0.0167
-8.000 -0.4405 0.02057 0.01522 -0.0801 0.7692 0.0118
-7.750 -0.4200 0.01898 0.01342 -0.0791 0.7680 0.0119
-7.500 -0.3972 0.01775 0.01202 -0.0785 0.7669 0.0119
-7.250 -0.3734 0.01692 0.01107 -0.0781 0.7659 0.0122
-7.000 -0.3489 0.01617 0.01023 -0.0777 0.7650 0.0124
-6.750 -0.3240 0.01546 0.00943 -0.0774 0.7641 0.0125
-6.500 -0.2991 0.01480 0.00870 -0.0771 0.7632 0.0126
-6.250 -0.2741 0.01430 0.00814 -0.0768 0.7622 0.0128
-6.000 -0.2493 0.01383 0.00762 -0.0765 0.7611 0.0129
-5.750 -0.2248 0.01340 0.00714 -0.0762 0.7598 0.0130
-5.500 -0.2045 0.01249 0.00619 -0.0751 0.7588 0.0134
-5.250 -0.1821 0.01195 0.00564 -0.0743 0.7580 0.0139
-5.000 -0.1583 0.01157 0.00525 -0.0738 0.7570 0.0144
-4.750 -0.1339 0.01124 0.00491 -0.0734 0.7559 0.0148
-4.500 -0.1091 0.01095 0.00459 -0.0730 0.7546 0.0153
-4.250 -0.0839 0.01069 0.00431 -0.0727 0.7533 0.0160
-4.000 -0.0581 0.01048 0.00408 -0.0726 0.7519 0.0166
-3.750 -0.0328 0.01021 0.00377 -0.0723 0.7505 0.0176
-3.500 -0.0069 0.00999 0.00355 -0.0721 0.7492 0.0194
-3.250 0.0196 0.00982 0.00336 -0.0720 0.7478 0.0216
-3.000 0.0425 0.00938 0.00315 -0.0714 0.7464 0.0730
-2.750 0.0642 0.00891 0.00302 -0.0707 0.7447 0.1673
-2.500 0.0846 0.00834 0.00290 -0.0698 0.7432 0.2881
-2.250 0.1044 0.00767 0.00273 -0.0689 0.7418 0.4275
-2.000 0.1225 0.00679 0.00250 -0.0677 0.7402 0.6098
-1.750 0.1433 0.00638 0.00270 -0.0663 0.7384 0.7832
-1.500 0.1724 0.00649 0.00278 -0.0666 0.7367 0.8029
-1.250 0.2013 0.00668 0.00294 -0.0668 0.7349 0.8167
-1.000 0.2292 0.00698 0.00325 -0.0665 0.7332 0.8274
-0.750 0.2582 0.00710 0.00333 -0.0667 0.7315 0.8329
-0.500 0.2858 0.00735 0.00359 -0.0665 0.7296 0.8380
-0.250 0.3138 0.00758 0.00381 -0.0664 0.7278 0.8440
0.000 0.3413 0.00767 0.00391 -0.0663 0.7260 0.8485
0.250 0.3678 0.00780 0.00406 -0.0659 0.7237 0.8518
0.500 0.3952 0.00791 0.00418 -0.0657 0.7213 0.8552
0.750 0.4237 0.00798 0.00422 -0.0659 0.7188 0.8588
1.000 0.4536 0.00804 0.00425 -0.0665 0.7163 0.8619
1.250 0.4805 0.00802 0.00421 -0.0663 0.7135 0.8638
1.500 0.5074 0.00797 0.00419 -0.0663 0.7109 0.8650
1.750 0.5352 0.00792 0.00415 -0.0664 0.7077 0.8660
2.000 0.5635 0.00786 0.00409 -0.0667 0.7043 0.8669
2.250 0.5921 0.00780 0.00401 -0.0671 0.7010 0.8677
2.500 0.6205 0.00777 0.00398 -0.0675 0.6974 0.8684
2.750 0.6483 0.00771 0.00395 -0.0677 0.6931 0.8693
3.000 0.6766 0.00763 0.00388 -0.0681 0.6885 0.8699
3.250 0.7051 0.00759 0.00382 -0.0685 0.6840 0.8706
3.500 0.7328 0.00753 0.00381 -0.0688 0.6777 0.8714
3.750 0.7607 0.00748 0.00374 -0.0691 0.6708 0.8720
4.000 0.7884 0.00744 0.00372 -0.0694 0.6613 0.8726
4.250 0.8154 0.00742 0.00369 -0.0695 0.6498 0.8731
4.500 0.8415 0.00744 0.00368 -0.0695 0.6348 0.8737
4.750 0.8658 0.00753 0.00370 -0.0691 0.6156 0.8745
5.000 0.8888 0.00768 0.00378 -0.0684 0.5949 0.8751
5.250 0.9106 0.00788 0.00389 -0.0676 0.5726 0.8756
5.500 0.9312 0.00812 0.00404 -0.0665 0.5502 0.8761
5.750 0.9512 0.00836 0.00421 -0.0654 0.5278 0.8765
6.000 0.9687 0.00861 0.00438 -0.0638 0.5034 0.8772
6.250 0.9828 0.00891 0.00457 -0.0615 0.4757 0.8779
6.500 0.9914 0.00927 0.00481 -0.0580 0.4448 0.8790
6.750 0.9935 0.00973 0.00512 -0.0534 0.4095 0.8801
7.000 1.0004 0.01025 0.00551 -0.0499 0.3800 0.8810
7.250 1.0073 0.01082 0.00596 -0.0466 0.3509 0.8819
7.500 1.0146 0.01144 0.00646 -0.0435 0.3231 0.8829
7.750 1.0243 0.01203 0.00696 -0.0410 0.2998 0.8837
8.000 1.0319 0.01276 0.00757 -0.0382 0.2720 0.8847
8.250 1.0406 0.01350 0.00820 -0.0358 0.2468 0.8856
8.500 1.0484 0.01434 0.00891 -0.0333 0.2199 0.8865
8.750 1.0573 0.01517 0.00962 -0.0311 0.1951 0.8873
9.000 1.0659 0.01606 0.01039 -0.0290 0.1694 0.8882
9.250 1.0756 0.01694 0.01116 -0.0270 0.1479 0.8892
9.500 1.0842 0.01789 0.01199 -0.0250 0.1251 0.8898
9.750 1.0943 0.01881 0.01281 -0.0233 0.1050 0.8904
10.000 1.1008 0.01994 0.01379 -0.0212 0.0806 0.8910
10.250 1.1079 0.02106 0.01479 -0.0193 0.0603 0.8916
10.500 1.1154 0.02218 0.01580 -0.0174 0.0427 0.8925
10.750 1.1171 0.02368 0.01715 -0.0150 0.0209 0.8935
11.000 1.1242 0.02491 0.01833 -0.0132 0.0125 0.8943
11.250 1.1372 0.02579 0.01925 -0.0121 0.0113 0.8950
11.500 1.1484 0.02681 0.02031 -0.0108 0.0101 0.8957
11.750 1.1594 0.02787 0.02141 -0.0097 0.0096 0.8965
12.000 1.1712 0.02891 0.02251 -0.0086 0.0092 0.8973
12.250 1.1838 0.02991 0.02357 -0.0077 0.0090 0.8981
12.500 1.1942 0.03109 0.02481 -0.0066 0.0085 0.8989
12.750 1.2045 0.03232 0.02611 -0.0056 0.0082 0.8997
13.000 1.2143 0.03361 0.02746 -0.0047 0.0080 0.9006
13.250 1.2219 0.03512 0.02902 -0.0036 0.0077 0.9014
13.500 1.2301 0.03660 0.03057 -0.0027 0.0076 0.9022
13.750 1.2336 0.03854 0.03259 -0.0015 0.0073 0.9032
14.000 1.2362 0.04064 0.03477 -0.0005 0.0072 0.9041
14.250 1.2345 0.04319 0.03744 0.0007 0.0070 0.9050
14.500 1.2427 0.04491 0.03922 0.0012 0.0069 0.9056
14.750 1.2487 0.04686 0.04126 0.0017 0.0068 0.9067
15.000 1.2524 0.04909 0.04358 0.0022 0.0068 0.9079
15.250 1.2558 0.05142 0.04599 0.0026 0.0068 0.9090
15.500 1.2586 0.05388 0.04855 0.0028 0.0066 0.9101
15.750 1.2611 0.05644 0.05120 0.0030 0.0065 0.9111
16.000 1.2648 0.05897 0.05381 0.0029 0.0064 0.9123
16.250 1.2667 0.06176 0.05670 0.0028 0.0062 0.9134
16.500 1.2680 0.06472 0.05975 0.0025 0.0061 0.9145
16.750 1.2668 0.06805 0.06318 0.0021 0.0061 0.9156
17.000 1.2682 0.07114 0.06636 0.0015 0.0060 0.9167
17.250 1.2671 0.07466 0.06998 0.0007 0.0059 0.9178
17.500 1.2658 0.07830 0.07371 -0.0002 0.0058 0.9188
17.750 1.2630 0.08222 0.07773 -0.0013 0.0057 0.9198
18.000 1.2597 0.08626 0.08186 -0.0025 0.0056 0.9211
18.250 1.2569 0.09028 0.08599 -0.0038 0.0056 0.9225
18.500 1.2543 0.09437 0.09018 -0.0053 0.0055 0.9240
18.750 1.2502 0.09873 0.09464 -0.0069 0.0055 0.9254
19.000 1.2453 0.10327 0.09927 -0.0088 0.0054 0.9269
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