EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 435 AIRFOIL (e435-il) Reynolds number: 200,000 Max Cl/Cd: 79.31 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e435-il-200000.txt Download as CSV file: xf-e435-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 435 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1977 0.12400 0.12050 -0.0797 0.9758 0.0429
-11.500 -0.1981 0.11765 0.11417 -0.0886 0.9725 0.0450
-11.250 -0.1942 0.11178 0.10832 -0.0938 0.9685 0.0456
-11.000 -0.1731 0.10908 0.10560 -0.0937 0.9645 0.0464
-10.750 -0.1547 0.10572 0.10223 -0.0963 0.9617 0.0476
-10.500 -0.1397 0.10139 0.09789 -0.1006 0.9594 0.0499
-10.000 -0.1498 0.08630 0.08287 -0.1181 0.9478 0.0537
-9.750 -0.1225 0.08472 0.08126 -0.1173 0.9465 0.0548
-9.500 -0.1016 0.08144 0.07796 -0.1204 0.9449 0.0566
-9.250 -0.0975 0.07684 0.07337 -0.1245 0.9377 0.0589
-7.750 -0.1777 0.03773 0.03194 -0.1485 0.8856 0.0326
-7.500 -0.1505 0.03385 0.02811 -0.1503 0.8834 0.0303
-7.250 -0.1515 0.03065 0.02428 -0.1461 0.8748 0.0266
-7.000 -0.1282 0.02817 0.02147 -0.1462 0.8709 0.0259
-6.750 -0.0989 0.02585 0.01878 -0.1469 0.8682 0.0254
-6.500 -0.0764 0.02441 0.01710 -0.1461 0.8639 0.0256
-6.250 -0.0601 0.02346 0.01599 -0.1441 0.8580 0.0262
-6.000 -0.0321 0.02231 0.01465 -0.1441 0.8547 0.0272
-5.750 -0.0023 0.02117 0.01354 -0.1448 0.8520 0.0299
-5.500 0.0207 0.02051 0.01283 -0.1442 0.8480 0.0336
-5.250 0.0353 0.02015 0.01250 -0.1422 0.8419 0.0371
-5.000 0.0611 0.01923 0.01161 -0.1423 0.8384 0.0437
-4.750 0.0916 0.01826 0.01068 -0.1435 0.8357 0.0623
-4.500 0.1151 0.01731 0.00998 -0.1438 0.8317 0.1039
-4.250 0.1331 0.01627 0.00958 -0.1437 0.8259 0.2264
-4.000 0.1617 0.01512 0.00970 -0.1452 0.8225 0.5414
-3.750 0.1936 0.01548 0.01000 -0.1453 0.8198 0.5950
-3.500 0.2263 0.01589 0.01028 -0.1455 0.8176 0.6230
-3.250 0.2381 0.01658 0.01099 -0.1422 0.8110 0.6378
-3.000 0.2621 0.01701 0.01137 -0.1408 0.8070 0.6525
-2.750 0.2907 0.01732 0.01161 -0.1402 0.8041 0.6659
-2.500 0.3221 0.01753 0.01171 -0.1403 0.8019 0.6786
-2.250 0.3348 0.01808 0.01227 -0.1372 0.7959 0.6875
-2.000 0.3556 0.01840 0.01258 -0.1353 0.7914 0.6980
-1.750 0.3834 0.01861 0.01272 -0.1348 0.7883 0.7110
-1.500 0.4108 0.01876 0.01282 -0.1338 0.7859 0.7189
-1.250 0.4316 0.01898 0.01299 -0.1331 0.7806 0.7270
-1.000 0.4506 0.01913 0.01313 -0.1313 0.7756 0.7309
-0.750 0.4809 0.01906 0.01299 -0.1318 0.7724 0.7355
-0.500 0.5186 0.01887 0.01268 -0.1341 0.7700 0.7407
-0.250 0.5433 0.01895 0.01272 -0.1339 0.7656 0.7444
0.000 0.5611 0.01912 0.01291 -0.1323 0.7598 0.7474
0.250 0.5922 0.01901 0.01274 -0.1330 0.7563 0.7507
0.500 0.6289 0.01882 0.01248 -0.1350 0.7538 0.7543
0.750 0.6576 0.01890 0.01250 -0.1358 0.7494 0.7582
1.000 0.6768 0.01904 0.01267 -0.1345 0.7432 0.7611
1.250 0.7081 0.01889 0.01250 -0.1353 0.7397 0.7638
1.500 0.7446 0.01869 0.01224 -0.1370 0.7370 0.7666
1.750 0.7646 0.01892 0.01250 -0.1360 0.7311 0.7701
2.000 0.7924 0.01894 0.01251 -0.1365 0.7258 0.7742
2.250 0.8276 0.01871 0.01225 -0.1380 0.7223 0.7770
2.500 0.8647 0.01847 0.01196 -0.1397 0.7195 0.7795
2.750 0.8758 0.01880 0.01240 -0.1370 0.7114 0.7828
3.000 0.9093 0.01862 0.01220 -0.1382 0.7071 0.7863
3.250 0.9491 0.01836 0.01189 -0.1406 0.7039 0.7904
3.500 0.9634 0.01861 0.01224 -0.1385 0.6962 0.7939
3.750 0.9936 0.01843 0.01208 -0.1389 0.6912 0.7970
4.000 1.0316 0.01814 0.01176 -0.1408 0.6876 0.8005
4.250 1.0473 0.01837 0.01209 -0.1390 0.6794 0.8048
4.500 1.0813 0.01813 0.01185 -0.1402 0.6741 0.8087
4.750 1.1085 0.01801 0.01177 -0.1401 0.6684 0.8125
5.000 1.1292 0.01801 0.01185 -0.1389 0.6607 0.8171
5.250 1.1676 0.01769 0.01151 -0.1409 0.6556 0.8216
5.500 1.1823 0.01782 0.01175 -0.1387 0.6465 0.8261
5.750 1.2154 0.01751 0.01144 -0.1395 0.6403 0.8303
6.000 1.2311 0.01760 0.01165 -0.1374 0.6309 0.8357
6.250 1.2660 0.01733 0.01135 -0.1388 0.6238 0.8410
6.500 1.2771 0.01741 0.01157 -0.1357 0.6135 0.8469
6.750 1.3028 0.01732 0.01152 -0.1353 0.6046 0.8533
7.000 1.3222 0.01726 0.01152 -0.1338 0.5941 0.8595
7.250 1.3366 0.01733 0.01168 -0.1314 0.5827 0.8668
7.500 1.3549 0.01733 0.01173 -0.1296 0.5712 0.8744
7.750 1.3719 0.01731 0.01173 -0.1276 0.5590 0.8835
8.000 1.3807 0.01741 0.01187 -0.1241 0.5456 0.8945
8.250 1.3874 0.01759 0.01212 -0.1203 0.5315 0.9088
8.500 1.3935 0.01777 0.01237 -0.1165 0.5168 0.9301
8.750 1.4043 0.01798 0.01262 -0.1138 0.5006 1.0000
9.000 1.4212 0.01854 0.01313 -0.1128 0.4825 1.0000
9.250 1.4341 0.01923 0.01378 -0.1111 0.4636 1.0000
9.500 1.4432 0.02006 0.01458 -0.1089 0.4440 1.0000
9.750 1.4506 0.02100 0.01546 -0.1065 0.4241 1.0000
10.000 1.4564 0.02205 0.01644 -0.1039 0.4045 1.0000
10.250 1.4608 0.02323 0.01753 -0.1012 0.3852 1.0000
10.500 1.4638 0.02454 0.01881 -0.0986 0.3655 1.0000
10.750 1.4662 0.02596 0.02019 -0.0960 0.3462 1.0000
11.000 1.4679 0.02750 0.02168 -0.0934 0.3275 1.0000
11.250 1.4688 0.02917 0.02329 -0.0910 0.3092 1.0000
11.500 1.4696 0.03094 0.02500 -0.0887 0.2916 1.0000
11.750 1.4702 0.03281 0.02681 -0.0866 0.2746 1.0000
12.000 1.4712 0.03474 0.02873 -0.0847 0.2576 1.0000
12.250 1.4720 0.03678 0.03075 -0.0829 0.2411 1.0000
12.500 1.4725 0.03892 0.03287 -0.0812 0.2254 1.0000
12.750 1.4727 0.04119 0.03512 -0.0796 0.2100 1.0000
13.000 1.4726 0.04356 0.03746 -0.0782 0.1954 1.0000
13.250 1.4723 0.04604 0.03993 -0.0770 0.1814 1.0000
13.500 1.4715 0.04867 0.04252 -0.0758 0.1682 1.0000
13.750 1.4711 0.05134 0.04519 -0.0748 0.1553 1.0000
14.000 1.4713 0.05405 0.04793 -0.0740 0.1431 1.0000
14.250 1.4713 0.05686 0.05076 -0.0733 0.1317 1.0000
14.500 1.4703 0.05987 0.05378 -0.0726 0.1212 1.0000
14.750 1.4672 0.06316 0.05704 -0.0721 0.1120 1.0000
15.000 1.4661 0.06636 0.06027 -0.0718 0.1028 1.0000
15.250 1.4653 0.06959 0.06357 -0.0716 0.0943 1.0000
15.500 1.4612 0.07328 0.06722 -0.0714 0.0872 1.0000
15.750 1.4605 0.07667 0.07071 -0.0715 0.0801 1.0000
16.000 1.4576 0.08036 0.07443 -0.0716 0.0741 1.0000
16.250 1.4551 0.08411 0.07823 -0.0720 0.0686 1.0000
16.500 1.4530 0.08783 0.08202 -0.0723 0.0636 1.0000
16.750 1.4509 0.09165 0.08590 -0.0729 0.0591 1.0000
17.000 1.4483 0.09549 0.08978 -0.0735 0.0552 1.0000
17.250 1.4470 0.09932 0.09371 -0.0743 0.0514 1.0000
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