EPPLER 603 AIRFOIL (e603-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 603 AIRFOIL (e603-il) Reynolds number: 200,000 Max Cl/Cd: 56.49 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e603-il-200000.txt Download as CSV file: xf-e603-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 603 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2318 0.09212 0.08844 -0.1087 0.8689 0.0685
-12.000 -0.2024 0.09163 0.08778 -0.1076 0.8512 0.0697
-11.750 -0.3101 0.05194 0.04760 -0.1181 0.8186 0.0402
-11.500 -0.3208 0.04782 0.04337 -0.1182 0.8125 0.0393
-11.250 -0.4038 0.05422 0.04936 -0.1223 0.8232 0.0422
-11.000 -0.4613 0.04705 0.04146 -0.1171 0.8138 0.0341
-10.750 -0.4667 0.04433 0.03852 -0.1150 0.8068 0.0338
-10.500 -0.4732 0.04182 0.03580 -0.1122 0.7995 0.0334
-10.250 -0.4782 0.03963 0.03331 -0.1092 0.7936 0.0330
-10.000 -0.4794 0.03758 0.03094 -0.1064 0.7879 0.0332
-9.750 -0.4736 0.03547 0.02854 -0.1042 0.7825 0.0332
-9.500 -0.4648 0.03362 0.02634 -0.1022 0.7780 0.0337
-9.250 -0.4527 0.03205 0.02436 -0.1005 0.7743 0.0342
-9.000 -0.4355 0.03040 0.02244 -0.0993 0.7701 0.0345
-8.750 -0.4062 0.02815 0.02002 -0.0998 0.7664 0.0352
-8.500 -0.3755 0.02670 0.01853 -0.1005 0.7630 0.0363
-8.250 -0.3464 0.02563 0.01736 -0.1008 0.7598 0.0378
-8.000 -0.3158 0.02471 0.01630 -0.1013 0.7568 0.0398
-7.750 -0.2842 0.02364 0.01526 -0.1020 0.7534 0.0429
-7.500 -0.2601 0.02300 0.01464 -0.1016 0.7498 0.0459
-7.250 -0.2351 0.02223 0.01381 -0.1012 0.7468 0.0494
-7.000 -0.2165 0.02158 0.01322 -0.1001 0.7441 0.0537
-6.750 -0.2003 0.02098 0.01261 -0.0987 0.7416 0.0604
-6.500 -0.1859 0.02054 0.01216 -0.0969 0.7390 0.0684
-6.250 -0.1769 0.02003 0.01174 -0.0944 0.7359 0.0789
-6.000 -0.1701 0.01941 0.01125 -0.0917 0.7326 0.0951
-5.750 -0.1614 0.01874 0.01076 -0.0893 0.7296 0.1241
-5.500 -0.1541 0.01795 0.01030 -0.0869 0.7271 0.1771
-5.250 -0.1492 0.01697 0.00982 -0.0844 0.7249 0.2751
-5.000 -0.1466 0.01572 0.00937 -0.0817 0.7227 0.4335
-4.750 -0.1308 0.01646 0.01110 -0.0776 0.7201 0.6153
-4.500 -0.1057 0.01723 0.01179 -0.0767 0.7171 0.6604
-4.250 -0.0789 0.01826 0.01272 -0.0755 0.7143 0.6824
-4.000 -0.0511 0.01944 0.01382 -0.0740 0.7120 0.6979
-3.750 -0.0238 0.02039 0.01466 -0.0729 0.7100 0.7113
-3.500 0.0088 0.02160 0.01579 -0.0715 0.7081 0.7162
-3.250 0.0336 0.02208 0.01613 -0.0709 0.7061 0.7288
-3.000 0.0628 0.02316 0.01723 -0.0691 0.7033 0.7322
-2.750 0.0921 0.02411 0.01814 -0.0679 0.7008 0.7403
-2.500 0.1214 0.02486 0.01885 -0.0669 0.6983 0.7497
-2.250 0.1413 0.02525 0.01918 -0.0654 0.6957 0.7628
-2.000 0.1856 0.02580 0.01964 -0.0665 0.6936 0.7667
-1.750 0.1974 0.02587 0.01964 -0.0645 0.6915 0.7784
-1.500 0.2385 0.02606 0.01974 -0.0658 0.6899 0.7815
-1.250 0.2692 0.02632 0.01999 -0.0661 0.6874 0.7860
-1.000 0.2629 0.02644 0.02015 -0.0613 0.6836 0.7961
-0.750 0.2936 0.02651 0.02020 -0.0616 0.6809 0.7989
-0.500 0.3208 0.02652 0.02018 -0.0616 0.6784 0.8027
-0.250 0.3224 0.02643 0.02004 -0.0583 0.6759 0.8107
0.000 0.3521 0.02625 0.01979 -0.0587 0.6740 0.8132
0.250 0.3846 0.02623 0.01970 -0.0595 0.6723 0.8155
0.500 0.3818 0.02665 0.02025 -0.0550 0.6674 0.8196
0.750 0.3859 0.02674 0.02036 -0.0519 0.6635 0.8242
1.000 0.4006 0.02661 0.02019 -0.0509 0.6607 0.8280
1.250 0.4289 0.02644 0.01998 -0.0510 0.6587 0.8296
1.500 0.4580 0.02626 0.01975 -0.0515 0.6569 0.8311
1.750 0.4666 0.02660 0.02013 -0.0489 0.6530 0.8339
2.000 0.4626 0.02711 0.02074 -0.0447 0.6470 0.8370
2.250 0.4870 0.02700 0.02060 -0.0450 0.6441 0.8388
2.500 0.5190 0.02678 0.02034 -0.0464 0.6422 0.8410
2.750 0.5537 0.02659 0.02009 -0.0485 0.6404 0.8427
3.000 0.5880 0.02640 0.01985 -0.0500 0.6388 0.8438
3.250 0.5576 0.02768 0.02133 -0.0418 0.6288 0.8463
3.500 0.5890 0.02744 0.02108 -0.0426 0.6266 0.8479
3.750 0.6259 0.02709 0.02070 -0.0444 0.6250 0.8492
4.000 0.6644 0.02674 0.02032 -0.0464 0.6234 0.8502
4.250 0.6388 0.02835 0.02210 -0.0399 0.6130 0.8528
4.500 0.6757 0.02802 0.02175 -0.0418 0.6107 0.8541
4.750 0.7176 0.02756 0.02127 -0.0444 0.6091 0.8555
5.000 0.7607 0.02708 0.02078 -0.0472 0.6075 0.8567
5.250 0.8057 0.02661 0.02028 -0.0504 0.6061 0.8575
5.500 0.7833 0.02816 0.02200 -0.0444 0.5951 0.8596
5.750 0.8255 0.02745 0.02130 -0.0466 0.5933 0.8603
6.000 0.8689 0.02672 0.02057 -0.0490 0.5915 0.8612
6.250 0.9139 0.02600 0.01983 -0.0516 0.5899 0.8624
6.500 0.8919 0.02728 0.02128 -0.0450 0.5795 0.8651
6.750 0.9363 0.02652 0.02054 -0.0476 0.5771 0.8660
7.000 0.9845 0.02566 0.01968 -0.0509 0.5751 0.8669
7.250 1.0327 0.02490 0.01891 -0.0542 0.5728 0.8678
7.500 1.0206 0.02581 0.02000 -0.0491 0.5630 0.8700
7.750 1.0697 0.02486 0.01905 -0.0524 0.5601 0.8710
8.000 1.1230 0.02389 0.01806 -0.0565 0.5575 0.8722
8.250 1.1138 0.02462 0.01896 -0.0517 0.5478 0.8746
8.500 1.1587 0.02362 0.01798 -0.0542 0.5439 0.8756
8.750 1.1665 0.02363 0.01810 -0.0513 0.5368 0.8773
9.000 1.1879 0.02322 0.01776 -0.0503 0.5302 0.8789
9.250 1.2192 0.02262 0.01720 -0.0509 0.5239 0.8804
9.500 1.2254 0.02276 0.01744 -0.0480 0.5150 0.8826
9.750 1.2431 0.02266 0.01740 -0.0468 0.5065 0.8850
10.000 1.2660 0.02241 0.01719 -0.0464 0.4972 0.8873
10.250 1.2708 0.02299 0.01787 -0.0441 0.4855 0.8896
10.500 1.2809 0.02323 0.01817 -0.0421 0.4740 0.8916
10.750 1.2937 0.02348 0.01843 -0.0405 0.4613 0.8938
11.000 1.3039 0.02399 0.01894 -0.0389 0.4472 0.8961
11.250 1.3101 0.02484 0.01981 -0.0371 0.4314 0.8987
11.500 1.3144 0.02596 0.02093 -0.0354 0.4144 0.9014
11.750 1.3175 0.02733 0.02227 -0.0339 0.3964 0.9043
12.000 1.3167 0.02871 0.02363 -0.0317 0.3789 0.9074
12.250 1.3159 0.03031 0.02519 -0.0297 0.3608 0.9106
12.500 1.3153 0.03208 0.02690 -0.0282 0.3426 0.9138
12.750 1.3143 0.03405 0.02879 -0.0269 0.3244 0.9169
13.000 1.3118 0.03619 0.03092 -0.0256 0.3067 0.9200
13.250 1.3084 0.03836 0.03305 -0.0242 0.2896 0.9236
13.500 1.3060 0.04063 0.03529 -0.0232 0.2731 0.9275
13.750 1.3041 0.04303 0.03766 -0.0224 0.2568 0.9316
14.000 1.3011 0.04548 0.04008 -0.0215 0.2413 0.9362
14.250 1.2981 0.04800 0.04258 -0.0207 0.2263 0.9421
14.500 1.2958 0.05061 0.04517 -0.0202 0.2117 0.9497
14.750 1.2940 0.05337 0.04793 -0.0201 0.1972 0.9616
15.000 1.2916 0.05613 0.05067 -0.0201 0.1839 1.0000
15.250 1.2917 0.05925 0.05376 -0.0207 0.1707 1.0000
15.500 1.2921 0.06244 0.05692 -0.0214 0.1585 1.0000
15.750 1.2940 0.06557 0.06007 -0.0223 0.1468 1.0000
16.000 1.2960 0.06871 0.06323 -0.0231 0.1361 1.0000
16.250 1.2962 0.07207 0.06657 -0.0240 0.1267 1.0000
16.500 1.2961 0.07555 0.07002 -0.0250 0.1176 1.0000
16.750 1.2979 0.07890 0.07344 -0.0260 0.1085 1.0000
17.000 1.2974 0.08249 0.07702 -0.0271 0.1010 1.0000
17.250 1.2972 0.08613 0.08069 -0.0283 0.0935 1.0000
17.500 1.2973 0.08977 0.08439 -0.0295 0.0863 1.0000
17.750 1.2944 0.09380 0.08836 -0.0308 0.0800 1.0000
18.000 1.2950 0.09750 0.09218 -0.0322 0.0735 1.0000
18.250 1.2913 0.10165 0.09627 -0.0337 0.0679 1.0000
18.500 1.2903 0.10568 0.10041 -0.0353 0.0622 1.0000
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Polar data table (+)
Polar graphs
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