EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 583 AIRFOIL (e583-il) Reynolds number: 200,000 Max Cl/Cd: 70.4 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e583-il-200000.txt Download as CSV file: xf-e583-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.1907 0.13015 0.12681 -0.0703 0.9748 0.0347
-12.250 -0.1893 0.12456 0.12122 -0.0785 0.9620 0.0359
-12.000 -0.1754 0.11905 0.11571 -0.0836 0.9524 0.0364
-11.750 -0.1468 0.11511 0.11172 -0.0863 0.9450 0.0372
-11.500 -0.1241 0.11072 0.10729 -0.0913 0.9365 0.0383
-11.250 -0.1044 0.10557 0.10209 -0.0980 0.9285 0.0407
-11.000 -0.1031 0.09796 0.09443 -0.1111 0.9172 0.0425
-10.750 -0.0800 0.09314 0.08955 -0.1148 0.9072 0.0432
-10.500 -0.0521 0.08995 0.08625 -0.1178 0.8968 0.0446
-10.250 -0.0377 0.08627 0.08249 -0.1215 0.8840 0.0460
-10.000 -0.0364 0.08197 0.07812 -0.1255 0.8713 0.0487
-9.750 -0.0579 0.07506 0.07118 -0.1339 0.8583 0.0500
-9.500 -0.0897 0.06946 0.06541 -0.1390 0.8468 0.0502
-9.250 -0.1126 0.06672 0.06256 -0.1385 0.8362 0.0502
-9.000 -0.0719 0.06347 0.05942 -0.1380 0.8327 0.0518
-8.750 -0.0789 0.06072 0.05663 -0.1380 0.8252 0.0522
-8.500 -0.0873 0.05817 0.05402 -0.1372 0.8184 0.0528
-8.250 -0.0979 0.05609 0.05186 -0.1352 0.8126 0.0542
-8.000 -0.1086 0.05382 0.04950 -0.1333 0.8062 0.0552
-7.750 -0.1475 0.05321 0.04820 -0.1281 0.7997 0.0591
-7.500 -0.1381 0.04832 0.04338 -0.1280 0.7958 0.0604
-7.250 -0.1252 0.04604 0.04115 -0.1272 0.7910 0.0617
-7.000 -0.1154 0.04411 0.03913 -0.1259 0.7869 0.0643
-6.750 -0.1339 0.03295 0.02647 -0.1184 0.7833 0.0299
-6.500 -0.1190 0.03050 0.02370 -0.1168 0.7801 0.0293
-6.250 -0.1047 0.02863 0.02145 -0.1148 0.7758 0.0298
-6.000 -0.0855 0.02685 0.01933 -0.1134 0.7718 0.0299
-5.750 -0.0624 0.02509 0.01728 -0.1125 0.7685 0.0296
-5.500 -0.0363 0.02346 0.01538 -0.1120 0.7659 0.0293
-5.250 -0.0110 0.02225 0.01397 -0.1113 0.7630 0.0296
-5.000 0.0122 0.02134 0.01294 -0.1103 0.7591 0.0303
-4.750 0.0354 0.02027 0.01192 -0.1096 0.7555 0.0319
-4.500 0.0589 0.01959 0.01121 -0.1088 0.7525 0.0347
-4.250 0.0818 0.01894 0.01057 -0.1081 0.7499 0.0400
-4.000 0.1039 0.01842 0.01005 -0.1072 0.7472 0.0498
-3.750 0.1193 0.01779 0.00959 -0.1052 0.7432 0.0709
-3.500 0.1350 0.01696 0.00915 -0.1036 0.7396 0.1367
-3.250 0.1474 0.01572 0.00884 -0.1019 0.7365 0.3343
-3.000 0.1527 0.01484 0.00950 -0.0968 0.7339 0.6930
-2.750 0.1758 0.01558 0.01015 -0.0945 0.7316 0.7666
-2.500 0.1915 0.01632 0.01087 -0.0913 0.7278 0.7933
-2.250 0.2089 0.01699 0.01150 -0.0881 0.7242 0.8124
-2.000 0.2286 0.01752 0.01195 -0.0853 0.7210 0.8291
-1.750 0.2509 0.01794 0.01226 -0.0830 0.7183 0.8443
-1.500 0.2754 0.01827 0.01247 -0.0813 0.7162 0.8583
-1.250 0.2928 0.01863 0.01277 -0.0789 0.7129 0.8713
-1.000 0.3142 0.01901 0.01314 -0.0767 0.7089 0.8827
-0.750 0.3408 0.01937 0.01344 -0.0754 0.7056 0.9021
-0.500 0.4217 0.01956 0.01345 -0.0847 0.7035 0.9135
-0.250 0.4554 0.01948 0.01326 -0.0860 0.7010 0.9191
0.000 0.5024 0.01940 0.01303 -0.0901 0.6989 0.9216
0.250 0.5162 0.01963 0.01330 -0.0881 0.6943 0.9274
0.500 0.5264 0.01970 0.01338 -0.0852 0.6902 0.9330
0.750 0.5638 0.01961 0.01321 -0.0875 0.6870 0.9351
1.000 0.5995 0.01949 0.01300 -0.0894 0.6845 0.9374
1.250 0.6318 0.01944 0.01285 -0.0906 0.6823 0.9399
1.500 0.6192 0.01983 0.01336 -0.0836 0.6762 0.9464
1.750 0.6511 0.01982 0.01333 -0.0849 0.6725 0.9482
2.000 0.6850 0.01970 0.01316 -0.0865 0.6695 0.9500
2.250 0.7186 0.01958 0.01298 -0.0879 0.6671 0.9516
2.500 0.7241 0.01990 0.01336 -0.0843 0.6620 0.9562
2.750 0.7326 0.02004 0.01353 -0.0812 0.6572 0.9597
3.000 0.7674 0.01994 0.01340 -0.0830 0.6539 0.9610
3.250 0.8069 0.01975 0.01315 -0.0855 0.6514 0.9621
3.500 0.8277 0.01996 0.01341 -0.0849 0.6468 0.9647
3.750 0.8399 0.02015 0.01365 -0.0826 0.6411 0.9681
4.000 0.8636 0.02003 0.01351 -0.0821 0.6376 0.9708
4.250 0.9037 0.01977 0.01322 -0.0846 0.6349 0.9719
4.500 0.9252 0.02006 0.01359 -0.0843 0.6290 0.9744
4.750 0.9512 0.02007 0.01365 -0.0845 0.6238 0.9766
5.000 0.9874 0.01981 0.01337 -0.0864 0.6204 0.9780
5.250 1.0278 0.01952 0.01303 -0.0889 0.6176 0.9788
5.500 1.0328 0.02000 0.01367 -0.0856 0.6097 0.9839
5.750 1.0713 0.01973 0.01342 -0.0880 0.6053 0.9853
6.000 1.1140 0.01938 0.01303 -0.0909 0.6021 0.9861
6.250 1.1273 0.01976 0.01358 -0.0892 0.5942 0.9905
6.500 1.1611 0.01948 0.01332 -0.0906 0.5893 0.9926
6.750 1.1997 0.01917 0.01298 -0.0929 0.5851 0.9939
7.000 1.2170 0.01942 0.01340 -0.0919 0.5767 0.9987
7.250 1.2527 0.01905 0.01302 -0.0935 0.5718 1.0000
7.500 1.2420 0.01924 0.01331 -0.0868 0.5650 1.0000
7.750 1.2441 0.01911 0.01321 -0.0822 0.5588 1.0000
8.000 1.2620 0.01885 0.01296 -0.0805 0.5531 1.0000
8.250 1.2564 0.01899 0.01321 -0.0750 0.5450 1.0000
8.500 1.2882 0.01868 0.01288 -0.0759 0.5383 1.0000
8.750 1.2931 0.01889 0.01320 -0.0725 0.5289 1.0000
9.000 1.3134 0.01888 0.01324 -0.0716 0.5204 1.0000
9.250 1.3319 0.01892 0.01331 -0.0704 0.5108 1.0000
9.500 1.3418 0.01926 0.01373 -0.0681 0.4999 1.0000
9.750 1.3586 0.01948 0.01398 -0.0668 0.4890 1.0000
10.000 1.3761 0.01970 0.01419 -0.0657 0.4771 1.0000
10.250 1.3867 0.02017 0.01467 -0.0636 0.4637 1.0000
10.500 1.3928 0.02090 0.01543 -0.0611 0.4501 1.0000
10.750 1.3992 0.02170 0.01626 -0.0588 0.4357 1.0000
11.000 1.4048 0.02262 0.01719 -0.0565 0.4211 1.0000
11.250 1.4090 0.02369 0.01825 -0.0542 0.4060 1.0000
11.500 1.4114 0.02491 0.01946 -0.0519 0.3904 1.0000
11.750 1.4129 0.02629 0.02082 -0.0496 0.3747 1.0000
12.000 1.4133 0.02781 0.02233 -0.0475 0.3587 1.0000
12.250 1.4127 0.02948 0.02398 -0.0453 0.3427 1.0000
12.500 1.4109 0.03132 0.02579 -0.0433 0.3263 1.0000
12.750 1.4088 0.03328 0.02772 -0.0414 0.3103 1.0000
13.000 1.4060 0.03538 0.02978 -0.0397 0.2944 1.0000
13.250 1.4032 0.03760 0.03197 -0.0381 0.2787 1.0000
13.500 1.3999 0.03995 0.03429 -0.0366 0.2632 1.0000
13.750 1.3967 0.04241 0.03673 -0.0353 0.2480 1.0000
14.000 1.3934 0.04498 0.03930 -0.0342 0.2331 1.0000
14.250 1.3898 0.04769 0.04199 -0.0333 0.2183 1.0000
14.500 1.3865 0.05047 0.04476 -0.0325 0.2041 1.0000
14.750 1.3833 0.05335 0.04764 -0.0318 0.1904 1.0000
15.000 1.3800 0.05632 0.05062 -0.0313 0.1769 1.0000
15.250 1.3765 0.05941 0.05371 -0.0309 0.1639 1.0000
15.500 1.3728 0.06262 0.05693 -0.0307 0.1517 1.0000
15.750 1.3684 0.06599 0.06030 -0.0305 0.1398 1.0000
16.000 1.3636 0.06949 0.06380 -0.0305 0.1287 1.0000
16.250 1.3576 0.07322 0.06749 -0.0307 0.1185 1.0000
16.500 1.3526 0.07697 0.07127 -0.0310 0.1081 1.0000
16.750 1.3482 0.08073 0.07507 -0.0314 0.0982 1.0000
17.000 1.3428 0.08467 0.07903 -0.0320 0.0895 1.0000
17.250 1.3350 0.08898 0.08331 -0.0327 0.0818 1.0000
17.500 1.3303 0.09303 0.08741 -0.0335 0.0741 1.0000
17.750 1.3250 0.09720 0.09163 -0.0345 0.0673 1.0000
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