EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER E662 AIRFOIL (e662-il) Reynolds number: 100,000 Max Cl/Cd: 40.88 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e662-il-100000-n5.txt Download as CSV file: xf-e662-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E662 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1758 0.12764 0.12229 -0.0973 0.9462 0.0567
-12.250 -0.1756 0.12403 0.11869 -0.1010 0.9429 0.0585
-12.000 -0.1838 0.11483 0.10950 -0.1067 0.9399 0.0392
-11.750 -0.1645 0.11242 0.10703 -0.1061 0.9382 0.0373
-11.500 -0.1559 0.10842 0.10300 -0.1085 0.9362 0.0358
-11.250 -0.1498 0.10379 0.09836 -0.1118 0.9343 0.0346
-11.000 -0.1435 0.09919 0.09375 -0.1154 0.9325 0.0349
-10.750 -0.1419 0.09471 0.08927 -0.1181 0.9295 0.0342
-10.500 -0.1416 0.09073 0.08531 -0.1203 0.9258 0.0349
-10.000 -0.1826 0.06876 0.06330 -0.1382 0.9184 0.0313
-9.750 -0.1986 0.06424 0.05871 -0.1406 0.9138 0.0311
-9.500 -0.2164 0.06110 0.05549 -0.1404 0.9080 0.0309
-9.250 -0.2345 0.05768 0.05193 -0.1404 0.9036 0.0308
-9.000 -0.2580 0.05636 0.05054 -0.1360 0.8981 0.0307
-8.750 -0.2785 0.05462 0.04867 -0.1318 0.8921 0.0306
-8.500 -0.2881 0.05175 0.04555 -0.1298 0.8885 0.0306
-8.250 -0.2990 0.04955 0.04311 -0.1264 0.8848 0.0305
-8.000 -0.3203 0.04868 0.04211 -0.1196 0.8780 0.0305
-7.750 -0.3220 0.04616 0.03926 -0.1171 0.8747 0.0305
-7.500 -0.3145 0.04329 0.03595 -0.1158 0.8725 0.0306
-7.250 -0.3289 0.04247 0.03493 -0.1094 0.8664 0.0307
-7.000 -0.3284 0.04084 0.03297 -0.1058 0.8623 0.0309
-6.750 -0.3132 0.03868 0.03033 -0.1047 0.8598 0.0313
-6.500 -0.2910 0.03701 0.02851 -0.1049 0.8581 0.0325
-6.250 -0.2650 0.03576 0.02708 -0.1054 0.8568 0.0341
-6.000 -0.2665 0.03540 0.02660 -0.1008 0.8518 0.0348
-5.750 -0.2546 0.03449 0.02547 -0.0985 0.8478 0.0357
-5.500 -0.2323 0.03328 0.02400 -0.0978 0.8455 0.0366
-5.250 -0.2066 0.03216 0.02264 -0.0976 0.8438 0.0377
-5.000 -0.1780 0.03115 0.02144 -0.0978 0.8423 0.0388
-4.750 -0.1487 0.03018 0.02047 -0.0985 0.8411 0.0410
-4.500 -0.1511 0.03033 0.02062 -0.0938 0.8348 0.0424
-4.250 -0.1311 0.02992 0.02015 -0.0927 0.8315 0.0456
-4.000 -0.1055 0.02939 0.01947 -0.0925 0.8292 0.0484
-3.750 -0.0778 0.02868 0.01879 -0.0930 0.8275 0.0526
-3.500 -0.0469 0.02812 0.01815 -0.0937 0.8261 0.0601
-3.250 -0.0416 0.02822 0.01830 -0.0904 0.8200 0.0685
-3.000 -0.0207 0.02786 0.01807 -0.0897 0.8164 0.0927
-2.750 0.0060 0.02737 0.01781 -0.0900 0.8139 0.1464
-2.500 0.0338 0.02638 0.01763 -0.0910 0.8121 0.3033
-2.250 0.0445 0.02540 0.01833 -0.0865 0.8103 0.6293
-2.000 0.0345 0.02635 0.01944 -0.0789 0.8018 0.7137
-1.750 0.0599 0.02677 0.01965 -0.0782 0.7987 0.7689
-1.500 0.0832 0.02713 0.01987 -0.0764 0.7963 0.8003
-1.250 0.0896 0.02769 0.02036 -0.0721 0.7905 0.8199
-1.000 0.0990 0.02806 0.02066 -0.0682 0.7850 0.8374
-0.750 0.1167 0.02818 0.02067 -0.0653 0.7819 0.8556
-0.500 0.1321 0.02817 0.02058 -0.0614 0.7798 0.8797
-0.250 0.1201 0.02858 0.02101 -0.0538 0.7701 0.9003
0.000 0.1353 0.02841 0.02076 -0.0502 0.7669 0.9232
0.250 0.1661 0.02825 0.02047 -0.0505 0.7650 0.9324
0.500 0.1734 0.02862 0.02079 -0.0479 0.7560 0.9383
0.750 0.2037 0.02857 0.02063 -0.0487 0.7528 0.9418
1.000 0.2375 0.02844 0.02038 -0.0500 0.7506 0.9447
1.500 0.2808 0.02878 0.02060 -0.0493 0.7384 0.9519
1.750 0.3160 0.02863 0.02038 -0.0509 0.7362 0.9542
2.000 0.3284 0.02908 0.02080 -0.0494 0.7270 0.9588
2.250 0.3618 0.02898 0.02066 -0.0507 0.7236 0.9611
2.500 0.3986 0.02879 0.02042 -0.0525 0.7214 0.9629
2.750 0.4138 0.02930 0.02094 -0.0516 0.7115 0.9670
3.000 0.4489 0.02910 0.02072 -0.0531 0.7085 0.9693
3.500 0.5034 0.02936 0.02098 -0.0544 0.6956 0.9762
3.750 0.5411 0.02899 0.02062 -0.0562 0.6931 0.9785
4.000 0.5587 0.02948 0.02114 -0.0558 0.6825 0.9852
4.250 0.5947 0.02902 0.02070 -0.0572 0.6795 0.9920
4.750 0.6430 0.02901 0.02076 -0.0570 0.6656 1.0000
5.000 0.6608 0.02939 0.02118 -0.0563 0.6556 1.0000
5.250 0.6938 0.02897 0.02079 -0.0571 0.6516 1.0000
5.750 0.7471 0.02879 0.02073 -0.0575 0.6372 1.0000
6.250 0.8038 0.02843 0.02048 -0.0581 0.6220 1.0000
6.500 0.8269 0.02861 0.02075 -0.0579 0.6113 1.0000
6.750 0.8641 0.02785 0.02006 -0.0590 0.6057 1.0000
7.000 0.8874 0.02803 0.02031 -0.0588 0.5935 1.0000
7.250 0.9152 0.02792 0.02029 -0.0591 0.5819 1.0000
7.500 0.9481 0.02749 0.01991 -0.0597 0.5710 1.0000
7.750 0.9822 0.02699 0.01945 -0.0605 0.5586 1.0000
8.000 1.0120 0.02680 0.01933 -0.0608 0.5431 1.0000
8.250 1.0391 0.02681 0.01936 -0.0609 0.5255 1.0000
8.500 1.0659 0.02685 0.01942 -0.0609 0.5062 1.0000
8.750 1.0937 0.02687 0.01943 -0.0610 0.4856 1.0000
9.000 1.1153 0.02728 0.01984 -0.0606 0.4638 1.0000
9.250 1.1357 0.02778 0.02030 -0.0600 0.4410 1.0000
9.500 1.1528 0.02849 0.02098 -0.0591 0.4177 1.0000
9.750 1.1684 0.02931 0.02176 -0.0581 0.3943 1.0000
10.000 1.1814 0.03030 0.02273 -0.0569 0.3708 1.0000
10.250 1.1933 0.03138 0.02374 -0.0557 0.3481 1.0000
10.500 1.2037 0.03259 0.02493 -0.0544 0.3255 1.0000
10.750 1.2129 0.03390 0.02619 -0.0530 0.3034 1.0000
11.000 1.2216 0.03530 0.02756 -0.0516 0.2819 1.0000
11.250 1.2290 0.03682 0.02907 -0.0503 0.2608 1.0000
11.500 1.2357 0.03843 0.03064 -0.0490 0.2415 1.0000
11.750 1.2425 0.04011 0.03232 -0.0478 0.2220 1.0000
12.000 1.2486 0.04188 0.03408 -0.0466 0.2041 1.0000
12.250 1.2535 0.04381 0.03599 -0.0454 0.1869 1.0000
12.500 1.2585 0.04579 0.03797 -0.0443 0.1715 1.0000
12.750 1.2633 0.04786 0.04005 -0.0434 0.1572 1.0000
13.000 1.2676 0.05002 0.04227 -0.0425 0.1438 1.0000
13.250 1.2720 0.05226 0.04455 -0.0417 0.1316 1.0000
13.500 1.2758 0.05462 0.04696 -0.0410 0.1207 1.0000
13.750 1.2782 0.05716 0.04954 -0.0404 0.1109 1.0000
14.000 1.2797 0.05987 0.05229 -0.0398 0.1021 1.0000
14.250 1.2827 0.06251 0.05504 -0.0394 0.0933 1.0000
14.500 1.2830 0.06551 0.05808 -0.0392 0.0854 1.0000
14.750 1.2823 0.06873 0.06135 -0.0391 0.0776 1.0000
15.000 1.2830 0.07188 0.06461 -0.0392 0.0697 1.0000
15.250 1.2799 0.07556 0.06834 -0.0395 0.0634 1.0000
15.500 1.2793 0.07905 0.07197 -0.0399 0.0567 1.0000
15.750 1.2759 0.08299 0.07598 -0.0405 0.0518 1.0000
16.000 1.2736 0.08690 0.08003 -0.0413 0.0469 1.0000
16.250 1.2675 0.09139 0.08457 -0.0423 0.0436 1.0000
16.500 1.2650 0.09549 0.08886 -0.0434 0.0396 1.0000
16.750 1.2584 0.10029 0.09376 -0.0449 0.0368 1.0000
17.000 1.2527 0.10503 0.09862 -0.0464 0.0343 1.0000
17.250 1.2483 0.10964 0.10340 -0.0481 0.0318 1.0000
17.500 1.2420 0.11467 0.10855 -0.0501 0.0299 1.0000
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