EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 583 AIRFOIL (e583-il) Reynolds number: 200,000 Max Cl/Cd: 69.95 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e583-il-200000-n5.txt Download as CSV file: xf-e583-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 583 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0845 0.09170 0.08728 -0.1125 0.8204 0.0114
-11.000 -0.0828 0.08788 0.08341 -0.1142 0.8110 0.0113
-10.750 -0.0821 0.08415 0.07965 -0.1159 0.8021 0.0111
-10.500 -0.0843 0.07986 0.07534 -0.1178 0.7948 0.0110
-10.250 -0.0889 0.07526 0.07073 -0.1200 0.7876 0.0107
-9.750 -0.1207 0.06057 0.05603 -0.1292 0.7750 0.0102
-9.500 -0.1564 0.05227 0.04757 -0.1326 0.7686 0.0100
-9.250 -0.2158 0.04338 0.03825 -0.1303 0.7625 0.0095
-9.000 -0.2458 0.03959 0.03412 -0.1255 0.7562 0.0094
-8.750 -0.2593 0.03623 0.03034 -0.1218 0.7512 0.0093
-8.500 -0.2614 0.03365 0.02738 -0.1190 0.7468 0.0093
-8.250 -0.2527 0.03233 0.02593 -0.1172 0.7419 0.0096
-8.000 -0.2453 0.03017 0.02342 -0.1151 0.7377 0.0097
-7.750 -0.2323 0.02858 0.02154 -0.1135 0.7341 0.0099
-7.500 -0.2166 0.02710 0.01975 -0.1121 0.7310 0.0102
-7.250 -0.1995 0.02568 0.01806 -0.1109 0.7272 0.0108
-7.000 -0.1805 0.02418 0.01612 -0.1096 0.7236 0.0118
-6.750 -0.1597 0.02315 0.01498 -0.1088 0.7201 0.0122
-6.500 -0.1375 0.02236 0.01404 -0.1082 0.7170 0.0129
-6.250 -0.1144 0.02133 0.01282 -0.1076 0.7142 0.0132
-6.000 -0.0919 0.02041 0.01178 -0.1068 0.7109 0.0137
-5.750 -0.0693 0.01962 0.01088 -0.1060 0.7078 0.0141
-5.500 -0.0471 0.01889 0.01005 -0.1052 0.7049 0.0147
-5.250 -0.0248 0.01829 0.00941 -0.1045 0.7021 0.0156
-5.000 -0.0018 0.01776 0.00879 -0.1038 0.6995 0.0167
-4.750 0.0205 0.01727 0.00823 -0.1030 0.6967 0.0182
-4.500 0.0432 0.01689 0.00781 -0.1023 0.6936 0.0214
-4.250 0.0662 0.01650 0.00743 -0.1017 0.6908 0.0262
-4.000 0.0893 0.01609 0.00702 -0.1010 0.6880 0.0344
-3.750 0.1125 0.01567 0.00665 -0.1004 0.6854 0.0515
-3.500 0.1362 0.01527 0.00634 -0.1000 0.6831 0.0824
-3.250 0.1584 0.01484 0.00614 -0.0994 0.6806 0.1336
-3.000 0.1788 0.01429 0.00595 -0.0987 0.6775 0.2199
-2.750 0.1973 0.01352 0.00574 -0.0977 0.6746 0.3635
-2.500 0.2116 0.01259 0.00576 -0.0955 0.6718 0.5887
-2.250 0.2316 0.01284 0.00635 -0.0929 0.6695 0.7159
-2.000 0.2576 0.01307 0.00647 -0.0922 0.6672 0.7504
-1.750 0.2835 0.01329 0.00658 -0.0916 0.6648 0.7725
-1.500 0.3069 0.01354 0.00680 -0.0905 0.6618 0.7868
-1.250 0.3304 0.01379 0.00700 -0.0893 0.6589 0.7989
-1.000 0.3514 0.01417 0.00735 -0.0871 0.6561 0.8172
-0.750 0.3717 0.01453 0.00768 -0.0847 0.6536 0.8336
-0.500 0.3966 0.01465 0.00770 -0.0840 0.6514 0.8421
-0.250 0.4232 0.01470 0.00766 -0.0838 0.6491 0.8451
0.000 0.4469 0.01474 0.00769 -0.0832 0.6458 0.8484
0.250 0.4725 0.01476 0.00767 -0.0831 0.6427 0.8517
0.500 0.4998 0.01477 0.00760 -0.0834 0.6397 0.8549
0.750 0.5268 0.01477 0.00754 -0.0835 0.6370 0.8568
1.000 0.5546 0.01479 0.00749 -0.0837 0.6347 0.8586
1.250 0.5802 0.01483 0.00751 -0.0835 0.6318 0.8604
1.500 0.6037 0.01489 0.00758 -0.0830 0.6282 0.8629
1.750 0.6295 0.01493 0.00761 -0.0829 0.6248 0.8652
2.000 0.6570 0.01495 0.00759 -0.0832 0.6218 0.8672
2.250 0.6859 0.01498 0.00756 -0.0838 0.6192 0.8693
2.500 0.7136 0.01503 0.00760 -0.0842 0.6163 0.8716
2.750 0.7352 0.01511 0.00773 -0.0832 0.6122 0.8735
3.000 0.7598 0.01517 0.00781 -0.0829 0.6085 0.8752
3.250 0.7863 0.01520 0.00783 -0.0830 0.6052 0.8769
3.500 0.8147 0.01522 0.00782 -0.0834 0.6024 0.8787
3.750 0.8375 0.01532 0.00797 -0.0828 0.5982 0.8812
4.000 0.8608 0.01541 0.00811 -0.0823 0.5937 0.8839
4.250 0.8875 0.01545 0.00816 -0.0825 0.5896 0.8862
4.500 0.9159 0.01545 0.00814 -0.0829 0.5863 0.8878
4.750 0.9347 0.01557 0.00835 -0.0815 0.5809 0.8900
5.000 0.9568 0.01563 0.00848 -0.0807 0.5759 0.8922
5.250 0.9827 0.01564 0.00849 -0.0806 0.5717 0.8943
5.500 1.0037 0.01575 0.00866 -0.0797 0.5663 0.8973
5.750 1.0247 0.01585 0.00884 -0.0788 0.5604 0.9005
6.000 1.0503 0.01586 0.00886 -0.0787 0.5557 0.9029
6.250 1.0665 0.01599 0.00909 -0.0769 0.5492 0.9057
6.500 1.0859 0.01606 0.00922 -0.0756 0.5429 0.9088
6.750 1.1066 0.01614 0.00935 -0.0746 0.5369 0.9120
7.000 1.1217 0.01629 0.00957 -0.0727 0.5293 0.9159
7.250 1.1400 0.01634 0.00965 -0.0712 0.5226 0.9195
7.500 1.1516 0.01655 0.00996 -0.0685 0.5143 0.9248
7.750 1.1689 0.01671 0.01015 -0.0670 0.5066 0.9300
8.000 1.1817 0.01695 0.01046 -0.0648 0.4973 0.9356
8.250 1.1958 0.01722 0.01079 -0.0628 0.4880 0.9423
8.750 1.2273 0.01789 0.01155 -0.0600 0.4670 0.9605
9.000 1.2461 0.01834 0.01205 -0.0596 0.4549 0.9821
9.250 1.2602 0.01889 0.01262 -0.0583 0.4429 1.0000
9.500 1.2730 0.01958 0.01330 -0.0570 0.4302 1.0000
9.750 1.2840 0.02038 0.01409 -0.0555 0.4168 1.0000
10.000 1.2935 0.02130 0.01503 -0.0539 0.4033 1.0000
10.250 1.3013 0.02234 0.01607 -0.0522 0.3888 1.0000
10.500 1.3073 0.02353 0.01724 -0.0505 0.3736 1.0000
10.750 1.3118 0.02486 0.01855 -0.0486 0.3579 1.0000
11.000 1.3160 0.02628 0.01995 -0.0469 0.3428 1.0000
11.250 1.3190 0.02783 0.02148 -0.0452 0.3274 1.0000
11.500 1.3217 0.02945 0.02310 -0.0436 0.3125 1.0000
11.750 1.3243 0.03116 0.02479 -0.0421 0.2981 1.0000
12.000 1.3255 0.03302 0.02663 -0.0406 0.2830 1.0000
12.250 1.3269 0.03492 0.02853 -0.0392 0.2688 1.0000
12.500 1.3281 0.03693 0.03052 -0.0379 0.2546 1.0000
12.750 1.3292 0.03901 0.03259 -0.0368 0.2407 1.0000
13.000 1.3297 0.04120 0.03478 -0.0357 0.2269 1.0000
13.250 1.3302 0.04347 0.03704 -0.0348 0.2131 1.0000
13.500 1.3301 0.04589 0.03943 -0.0339 0.1992 1.0000
13.750 1.3299 0.04837 0.04191 -0.0332 0.1861 1.0000
14.000 1.3293 0.05095 0.04448 -0.0325 0.1733 1.0000
14.250 1.3290 0.05360 0.04712 -0.0320 0.1603 1.0000
14.500 1.3292 0.05627 0.04979 -0.0316 0.1480 1.0000
14.750 1.3295 0.05899 0.05253 -0.0313 0.1366 1.0000
15.000 1.3294 0.06182 0.05537 -0.0311 0.1257 1.0000
15.250 1.3287 0.06479 0.05836 -0.0310 0.1160 1.0000
15.500 1.3273 0.06790 0.06148 -0.0311 0.1068 1.0000
15.750 1.3279 0.07084 0.06446 -0.0312 0.0975 1.0000
16.000 1.3271 0.07402 0.06768 -0.0314 0.0894 1.0000
16.250 1.3252 0.07741 0.07109 -0.0317 0.0821 1.0000
16.500 1.3246 0.08069 0.07444 -0.0321 0.0745 1.0000
16.750 1.3229 0.08418 0.07798 -0.0327 0.0680 1.0000
17.000 1.3195 0.08794 0.08177 -0.0334 0.0622 1.0000
17.250 1.3186 0.09144 0.08534 -0.0341 0.0563 1.0000
17.500 1.3151 0.09536 0.08931 -0.0350 0.0514 1.0000
17.750 1.3128 0.09918 0.09321 -0.0361 0.0467 1.0000
18.000 1.3098 0.10313 0.09723 -0.0372 0.0426 1.0000
18.250 1.3060 0.10725 0.10141 -0.0385 0.0388 1.0000
18.500 1.3029 0.11133 0.10559 -0.0399 0.0355 1.0000
18.750 1.2988 0.11562 0.10995 -0.0414 0.0326 1.0000
19.000 1.2954 0.11982 0.11424 -0.0430 0.0300 1.0000
19.250 1.2916 0.12412 0.11864 -0.0448 0.0276 1.0000
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