EPPLER 604 AIRFOIL (e604-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 604 AIRFOIL (e604-il) Reynolds number: 500,000 Max Cl/Cd: 101.85 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e604-il-500000-n5.txt Download as CSV file: xf-e604-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 604 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -0.5444 0.11443 0.11157 -0.0697 1.0000 0.0050
-16.750 -0.6074 0.09754 0.09439 -0.0776 1.0000 0.0049
-16.500 -0.6398 0.08757 0.08421 -0.0825 1.0000 0.0047
-16.250 -0.6655 0.07938 0.07586 -0.0865 1.0000 0.0047
-16.000 -0.6844 0.07170 0.06802 -0.0914 0.9995 0.0048
-15.750 -0.6902 0.06520 0.06135 -0.0969 0.9977 0.0048
-15.250 -0.6939 0.05523 0.05106 -0.1048 0.9895 0.0048
-15.000 -0.6926 0.05117 0.04686 -0.1081 0.9835 0.0048
-14.500 -0.6873 0.04450 0.03995 -0.1124 0.9592 0.0050
-14.250 -0.6726 0.04138 0.03667 -0.1165 0.9478 0.0050
-14.000 -0.6485 0.03854 0.03367 -0.1218 0.9392 0.0050
-13.750 -0.6186 0.03581 0.03078 -0.1280 0.9306 0.0052
-13.500 -0.5872 0.03334 0.02811 -0.1340 0.9186 0.0053
-13.250 -0.5577 0.03146 0.02605 -0.1386 0.9017 0.0054
-13.000 -0.5393 0.02998 0.02436 -0.1403 0.8824 0.0054
-12.750 -0.5287 0.02869 0.02290 -0.1401 0.8652 0.0057
-12.500 -0.5196 0.02756 0.02162 -0.1393 0.8510 0.0058
-12.250 -0.5096 0.02658 0.02050 -0.1384 0.8393 0.0061
-12.000 -0.4999 0.02562 0.01941 -0.1373 0.8291 0.0061
-11.750 -0.4897 0.02471 0.01840 -0.1361 0.8197 0.0061
-11.500 -0.4783 0.02389 0.01746 -0.1350 0.8115 0.0062
-11.250 -0.4668 0.02308 0.01656 -0.1338 0.8033 0.0063
-11.000 -0.4563 0.02224 0.01563 -0.1325 0.7959 0.0066
-10.750 -0.4437 0.02151 0.01484 -0.1313 0.7886 0.0071
-10.500 -0.4304 0.02085 0.01410 -0.1301 0.7817 0.0072
-10.250 -0.4165 0.02023 0.01341 -0.1289 0.7755 0.0074
-10.000 -0.4027 0.01959 0.01270 -0.1276 0.7694 0.0078
-9.750 -0.3885 0.01903 0.01205 -0.1264 0.7640 0.0082
-9.500 -0.3735 0.01847 0.01144 -0.1252 0.7589 0.0085
-9.250 -0.3596 0.01789 0.01082 -0.1238 0.7535 0.0091
-9.000 -0.3453 0.01737 0.01024 -0.1224 0.7484 0.0097
-8.750 -0.3303 0.01688 0.00970 -0.1211 0.7436 0.0106
-8.500 -0.3162 0.01637 0.00916 -0.1195 0.7387 0.0115
-8.250 -0.3025 0.01592 0.00866 -0.1179 0.7341 0.0129
-8.000 -0.2905 0.01552 0.00822 -0.1159 0.7302 0.0147
-7.750 -0.2780 0.01516 0.00784 -0.1139 0.7261 0.0166
-7.500 -0.2617 0.01476 0.00743 -0.1127 0.7219 0.0189
-7.250 -0.2437 0.01442 0.00705 -0.1116 0.7179 0.0220
-7.000 -0.2245 0.01410 0.00670 -0.1107 0.7142 0.0258
-6.750 -0.2042 0.01377 0.00638 -0.1099 0.7107 0.0305
-6.500 -0.1831 0.01345 0.00607 -0.1092 0.7073 0.0363
-6.250 -0.1615 0.01314 0.00577 -0.1087 0.7039 0.0437
-6.000 -0.1396 0.01283 0.00548 -0.1081 0.7007 0.0549
-5.750 -0.1169 0.01253 0.00520 -0.1077 0.6976 0.0691
-5.500 -0.0939 0.01218 0.00493 -0.1074 0.6943 0.0871
-5.250 -0.0702 0.01185 0.00468 -0.1073 0.6911 0.1085
-4.750 -0.0225 0.01108 0.00414 -0.1071 0.6852 0.1780
-4.500 0.0017 0.01062 0.00384 -0.1072 0.6824 0.2341
-4.250 0.0256 0.00992 0.00348 -0.1075 0.6795 0.3227
-4.000 0.0500 0.00894 0.00305 -0.1082 0.6767 0.4630
-3.750 0.0778 0.00868 0.00303 -0.1087 0.6737 0.5424
-3.500 0.1065 0.00868 0.00303 -0.1090 0.6708 0.5668
-3.250 0.1354 0.00870 0.00301 -0.1093 0.6681 0.5808
-2.750 0.1934 0.00878 0.00301 -0.1101 0.6631 0.6023
-2.500 0.2222 0.00884 0.00306 -0.1104 0.6602 0.6137
-2.250 0.2513 0.00893 0.00311 -0.1108 0.6573 0.6258
-2.000 0.2796 0.00903 0.00322 -0.1109 0.6546 0.6340
-1.750 0.3087 0.00910 0.00321 -0.1113 0.6519 0.6395
-1.500 0.3378 0.00914 0.00317 -0.1118 0.6495 0.6416
-1.250 0.3663 0.00913 0.00317 -0.1121 0.6468 0.6433
-1.000 0.3949 0.00914 0.00317 -0.1125 0.6440 0.6448
-0.750 0.4234 0.00916 0.00317 -0.1128 0.6411 0.6464
-0.500 0.4520 0.00919 0.00317 -0.1131 0.6383 0.6481
-0.250 0.4806 0.00923 0.00318 -0.1135 0.6356 0.6501
0.000 0.5093 0.00928 0.00318 -0.1139 0.6330 0.6520
0.250 0.5378 0.00930 0.00320 -0.1142 0.6301 0.6538
0.500 0.5662 0.00933 0.00322 -0.1146 0.6271 0.6556
0.750 0.5945 0.00936 0.00323 -0.1149 0.6238 0.6572
1.000 0.6226 0.00940 0.00326 -0.1152 0.6208 0.6588
1.250 0.6506 0.00946 0.00330 -0.1154 0.6179 0.6605
1.500 0.6784 0.00950 0.00336 -0.1157 0.6149 0.6622
1.750 0.7061 0.00954 0.00343 -0.1159 0.6114 0.6639
2.000 0.7337 0.00959 0.00349 -0.1160 0.6079 0.6656
2.250 0.7612 0.00965 0.00354 -0.1162 0.6044 0.6674
2.500 0.7888 0.00972 0.00359 -0.1164 0.6011 0.6692
2.750 0.8159 0.00976 0.00367 -0.1165 0.5971 0.6711
3.000 0.8428 0.00982 0.00374 -0.1166 0.5925 0.6730
3.250 0.8692 0.00989 0.00380 -0.1165 0.5878 0.6749
3.500 0.8953 0.00996 0.00389 -0.1164 0.5832 0.6766
3.750 0.9211 0.01001 0.00400 -0.1163 0.5778 0.6784
4.000 0.9462 0.01010 0.00409 -0.1160 0.5722 0.6802
4.250 0.9714 0.01018 0.00420 -0.1157 0.5664 0.6820
4.500 0.9959 0.01026 0.00431 -0.1153 0.5596 0.6840
4.750 1.0197 0.01038 0.00441 -0.1148 0.5533 0.6861
5.000 1.0438 0.01047 0.00454 -0.1143 0.5459 0.6881
5.250 1.0658 0.01062 0.00466 -0.1134 0.5383 0.6902
5.500 1.0883 0.01073 0.00481 -0.1126 0.5296 0.6921
5.750 1.1069 0.01087 0.00497 -0.1111 0.5203 0.6942
6.000 1.1244 0.01104 0.00515 -0.1093 0.5098 0.6964
6.250 1.1422 0.01123 0.00536 -0.1076 0.4992 0.6986
6.500 1.1585 0.01150 0.00561 -0.1057 0.4877 0.7010
6.750 1.1730 0.01182 0.00591 -0.1035 0.4744 0.7033
7.250 1.1995 0.01262 0.00663 -0.0989 0.4447 0.7080
7.500 1.2097 0.01311 0.00710 -0.0962 0.4274 0.7101
7.750 1.2200 0.01364 0.00761 -0.0936 0.4112 0.7124
8.000 1.2284 0.01428 0.00821 -0.0907 0.3931 0.7149
8.250 1.2356 0.01501 0.00890 -0.0879 0.3748 0.7178
8.500 1.2422 0.01583 0.00967 -0.0851 0.3567 0.7208
8.750 1.2466 0.01681 0.01058 -0.0821 0.3371 0.7236
9.000 1.2517 0.01781 0.01154 -0.0794 0.3196 0.7261
9.250 1.2559 0.01892 0.01261 -0.0767 0.3020 0.7285
9.500 1.2605 0.02009 0.01374 -0.0742 0.2843 0.7312
9.750 1.2646 0.02136 0.01496 -0.0718 0.2665 0.7341
10.000 1.2694 0.02266 0.01623 -0.0696 0.2503 0.7370
10.250 1.2742 0.02402 0.01754 -0.0676 0.2346 0.7399
10.500 1.2792 0.02541 0.01891 -0.0657 0.2198 0.7426
10.750 1.2840 0.02686 0.02033 -0.0639 0.2055 0.7455
11.000 1.2887 0.02837 0.02182 -0.0621 0.1910 0.7488
11.250 1.2934 0.02994 0.02337 -0.0605 0.1773 0.7522
11.500 1.2984 0.03155 0.02495 -0.0590 0.1648 0.7555
11.750 1.3050 0.03310 0.02649 -0.0578 0.1531 0.7585
12.000 1.3115 0.03467 0.02807 -0.0566 0.1425 0.7616
12.250 1.3172 0.03636 0.02976 -0.0554 0.1323 0.7649
12.500 1.3224 0.03815 0.03153 -0.0543 0.1221 0.7685
12.750 1.3283 0.03992 0.03330 -0.0533 0.1121 0.7720
13.000 1.3346 0.04170 0.03509 -0.0525 0.1033 0.7755
13.250 1.3398 0.04360 0.03701 -0.0516 0.0951 0.7794
13.500 1.3460 0.04548 0.03891 -0.0509 0.0875 0.7838
13.750 1.3523 0.04739 0.04084 -0.0503 0.0807 0.7883
14.000 1.3579 0.04941 0.04288 -0.0497 0.0748 0.7925
14.250 1.3645 0.05134 0.04488 -0.0492 0.0693 0.7972
14.500 1.3689 0.05357 0.04712 -0.0487 0.0636 0.8021
15.000 1.3792 0.05795 0.05159 -0.0479 0.0539 0.8123
15.250 1.3851 0.06012 0.05382 -0.0477 0.0497 0.8184
15.500 1.3884 0.06262 0.05637 -0.0475 0.0456 0.8247
15.750 1.3933 0.06495 0.05877 -0.0473 0.0418 0.8325
16.000 1.3957 0.06763 0.06151 -0.0472 0.0383 0.8407
16.250 1.3999 0.07009 0.06406 -0.0472 0.0353 0.8511
16.500 1.4017 0.07284 0.06689 -0.0471 0.0324 0.8634
16.750 1.4043 0.07554 0.06970 -0.0472 0.0299 0.8803
17.000 1.4053 0.07817 0.07247 -0.0469 0.0277 0.9226
17.500 1.4085 0.08412 0.07856 -0.0478 0.0237 1.0000
17.750 1.4084 0.08754 0.08202 -0.0484 0.0218 1.0000
18.000 1.4105 0.09070 0.08527 -0.0492 0.0204 1.0000
18.250 1.4112 0.09410 0.08872 -0.0500 0.0188 1.0000
18.500 1.4104 0.09776 0.09244 -0.0510 0.0175 1.0000
18.750 1.4112 0.10121 0.09598 -0.0520 0.0162 1.0000
19.000 1.4105 0.10491 0.09974 -0.0532 0.0151 1.0000
19.250 1.4089 0.10878 0.10369 -0.0545 0.0142 1.0000
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