EPPLER 584 AIRFOIL (e584-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 584 AIRFOIL (e584-il) Reynolds number: 200,000 Max Cl/Cd: 67.84 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e584-il-200000.txt Download as CSV file: xf-e584-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 584 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 -0.1834 0.12851 0.12516 -0.0735 0.9639 0.0374
-12.250 -0.1804 0.12303 0.11969 -0.0821 0.9504 0.0384
-12.000 -0.1626 0.11736 0.11399 -0.0874 0.9412 0.0390
-11.750 -0.1314 0.11314 0.10972 -0.0911 0.9327 0.0400
-11.500 -0.1058 0.10838 0.10488 -0.0974 0.9233 0.0414
-11.250 -0.0838 0.10303 0.09946 -0.1051 0.9135 0.0433
-11.000 -0.0877 0.09482 0.09119 -0.1201 0.8988 0.0452
-10.750 -0.0568 0.09116 0.08743 -0.1212 0.8873 0.0461
-10.500 -0.0341 0.08817 0.08432 -0.1238 0.8746 0.0473
-10.250 -0.0228 0.08474 0.08078 -0.1268 0.8625 0.0487
-10.000 -0.0241 0.08089 0.07689 -0.1295 0.8509 0.0512
-9.750 -0.0464 0.07452 0.07050 -0.1369 0.8401 0.0526
-9.500 -0.0765 0.06925 0.06508 -0.1413 0.8304 0.0528
-9.250 -0.1051 0.06650 0.06220 -0.1404 0.8218 0.0529
-9.000 -0.0794 0.06247 0.05828 -0.1408 0.8174 0.0541
-8.750 -0.0703 0.06054 0.05631 -0.1401 0.8127 0.0551
-8.500 -0.0793 0.05812 0.05385 -0.1388 0.8073 0.0559
-8.250 -0.0929 0.05604 0.05172 -0.1362 0.8019 0.0567
-8.000 -0.1014 0.05384 0.04939 -0.1341 0.7975 0.0580
-7.750 -0.1455 0.05367 0.04854 -0.1273 0.7925 0.0619
-7.250 -0.1193 0.04644 0.04150 -0.1267 0.7850 0.0645
-7.000 -0.1100 0.04451 0.03947 -0.1251 0.7815 0.0666
-6.750 -0.1172 0.04294 0.03731 -0.1211 0.7782 0.0735
-6.500 -0.1215 0.03217 0.02537 -0.1143 0.7753 0.0334
-6.250 -0.1077 0.02877 0.02138 -0.1114 0.7719 0.0277
-6.000 -0.0874 0.02682 0.01928 -0.1104 0.7688 0.0269
-5.750 -0.0649 0.02500 0.01717 -0.1093 0.7658 0.0263
-5.500 -0.0390 0.02341 0.01528 -0.1087 0.7631 0.0260
-5.250 -0.0111 0.02216 0.01377 -0.1085 0.7607 0.0266
-5.000 0.0117 0.02128 0.01279 -0.1075 0.7573 0.0274
-4.750 0.0344 0.02040 0.01194 -0.1067 0.7541 0.0293
-4.500 0.0577 0.01996 0.01143 -0.1059 0.7509 0.0331
-4.250 0.0805 0.01930 0.01080 -0.1051 0.7481 0.0377
-4.000 0.1025 0.01859 0.01011 -0.1041 0.7455 0.0437
-3.750 0.1210 0.01804 0.00964 -0.1026 0.7429 0.0595
-3.500 0.1333 0.01735 0.00928 -0.1000 0.7391 0.1057
-3.250 0.1443 0.01646 0.00904 -0.0977 0.7355 0.2326
-3.000 0.1457 0.01501 0.00887 -0.0936 0.7325 0.5214
-2.750 0.1597 0.01592 0.01066 -0.0876 0.7302 0.7890
-2.500 0.1832 0.01691 0.01149 -0.0850 0.7280 0.8261
-2.250 0.2036 0.01783 0.01236 -0.0821 0.7244 0.8462
-2.000 0.2342 0.01861 0.01305 -0.0811 0.7211 0.8648
-1.750 0.2837 0.01920 0.01348 -0.0839 0.7183 0.8818
-1.500 0.3632 0.01949 0.01353 -0.0931 0.7162 0.8950
-1.250 0.4430 0.01964 0.01347 -0.1025 0.7142 0.9132
-1.000 0.4993 0.01974 0.01339 -0.1078 0.7122 0.9312
-0.750 0.5496 0.01962 0.01322 -0.1126 0.7089 0.9406
-0.500 0.5813 0.01959 0.01314 -0.1139 0.7053 0.9487
-0.250 0.6151 0.01950 0.01299 -0.1156 0.7021 0.9556
0.000 0.6506 0.01930 0.01270 -0.1176 0.6993 0.9612
0.250 0.6886 0.01911 0.01241 -0.1201 0.6970 0.9660
0.500 0.7094 0.01928 0.01261 -0.1194 0.6931 0.9717
0.750 0.7430 0.01916 0.01247 -0.1213 0.6892 0.9756
1.000 0.7726 0.01909 0.01236 -0.1222 0.6860 0.9794
1.250 0.8017 0.01903 0.01223 -0.1229 0.6833 0.9828
1.500 0.8344 0.01894 0.01213 -0.1246 0.6800 0.9855
1.750 0.8589 0.01906 0.01229 -0.1247 0.6754 0.9885
2.000 0.8867 0.01904 0.01225 -0.1253 0.6718 0.9910
2.250 0.9170 0.01896 0.01212 -0.1262 0.6689 0.9931
2.500 0.9454 0.01903 0.01220 -0.1270 0.6652 0.9951
2.750 0.9669 0.01921 0.01245 -0.1264 0.6601 0.9969
3.000 0.9964 0.01917 0.01239 -0.1273 0.6564 0.9987
3.250 1.0294 0.01909 0.01226 -0.1287 0.6535 1.0000
3.500 1.0386 0.01955 0.01282 -0.1258 0.6478 1.0000
3.750 1.0576 0.01969 0.01299 -0.1245 0.6432 1.0000
4.000 1.0845 0.01964 0.01290 -0.1246 0.6398 1.0000
4.250 1.0949 0.02003 0.01338 -0.1218 0.6342 1.0000
4.500 1.1117 0.02017 0.01358 -0.1200 0.6289 1.0000
4.750 1.1394 0.02005 0.01342 -0.1202 0.6254 1.0000
5.000 1.1461 0.02043 0.01392 -0.1167 0.6192 1.0000
5.250 1.1639 0.02046 0.01400 -0.1151 0.6141 1.0000
5.500 1.1936 0.02022 0.01373 -0.1156 0.6107 1.0000
5.750 1.1929 0.02066 0.01432 -0.1107 0.6036 1.0000
6.000 1.2144 0.02049 0.01418 -0.1096 0.5990 1.0000
6.250 1.2422 0.02020 0.01389 -0.1097 0.5953 1.0000
6.500 1.2385 0.02056 0.01440 -0.1042 0.5878 1.0000
6.750 1.2649 0.02015 0.01400 -0.1040 0.5835 1.0000
7.000 1.2714 0.02024 0.01417 -0.1002 0.5774 1.0000
7.250 1.2831 0.02013 0.01413 -0.0973 0.5714 1.0000
7.500 1.3156 0.01956 0.01354 -0.0981 0.5670 1.0000
7.750 1.3027 0.01994 0.01405 -0.0908 0.5590 1.0000
8.000 1.3262 0.01955 0.01367 -0.0900 0.5532 1.0000
8.250 1.3202 0.01972 0.01393 -0.0839 0.5460 1.0000
8.500 1.3281 0.01958 0.01381 -0.0803 0.5388 1.0000
8.750 1.3229 0.01959 0.01386 -0.0743 0.5317 1.0000
9.000 1.3010 0.01959 0.01390 -0.0652 0.5245 1.0000
9.250 1.3000 0.01947 0.01378 -0.0600 0.5172 1.0000
9.500 1.2810 0.01964 0.01401 -0.0520 0.5089 1.0000
9.750 1.2878 0.01977 0.01417 -0.0489 0.4993 1.0000
10.000 1.3079 0.01973 0.01412 -0.0480 0.4891 1.0000
10.250 1.3084 0.02036 0.01484 -0.0446 0.4770 1.0000
10.500 1.3176 0.02091 0.01543 -0.0426 0.4646 1.0000
10.750 1.3294 0.02146 0.01600 -0.0410 0.4518 1.0000
11.000 1.3406 0.02211 0.01665 -0.0395 0.4383 1.0000
11.250 1.3485 0.02296 0.01750 -0.0377 0.4237 1.0000
11.500 1.3549 0.02397 0.01850 -0.0360 0.4088 1.0000
11.750 1.3588 0.02519 0.01971 -0.0341 0.3934 1.0000
12.000 1.3621 0.02653 0.02105 -0.0323 0.3779 1.0000
12.250 1.3631 0.02807 0.02259 -0.0304 0.3620 1.0000
12.500 1.3637 0.02974 0.02425 -0.0287 0.3462 1.0000
12.750 1.3633 0.03156 0.02606 -0.0271 0.3301 1.0000
13.000 1.3628 0.03347 0.02795 -0.0256 0.3145 1.0000
13.250 1.3616 0.03553 0.02999 -0.0242 0.2987 1.0000
13.500 1.3598 0.03774 0.03219 -0.0229 0.2830 1.0000
13.750 1.3581 0.04003 0.03446 -0.0218 0.2678 1.0000
14.000 1.3557 0.04247 0.03687 -0.0207 0.2525 1.0000
14.250 1.3530 0.04501 0.03939 -0.0198 0.2376 1.0000
14.500 1.3503 0.04765 0.04201 -0.0190 0.2231 1.0000
14.750 1.3474 0.05039 0.04475 -0.0184 0.2088 1.0000
15.000 1.3450 0.05318 0.04756 -0.0179 0.1951 1.0000
15.250 1.3421 0.05610 0.05049 -0.0175 0.1817 1.0000
15.500 1.3390 0.05912 0.05352 -0.0172 0.1688 1.0000
15.750 1.3353 0.06231 0.05671 -0.0170 0.1563 1.0000
16.000 1.3314 0.06560 0.05999 -0.0170 0.1448 1.0000
16.250 1.3267 0.06905 0.06342 -0.0170 0.1339 1.0000
16.500 1.3218 0.07265 0.06702 -0.0173 0.1231 1.0000
16.750 1.3180 0.07624 0.07065 -0.0176 0.1125 1.0000
17.000 1.3135 0.07996 0.07440 -0.0181 0.1029 1.0000
17.250 1.3075 0.08391 0.07834 -0.0187 0.0944 1.0000
17.500 1.3009 0.08805 0.08248 -0.0195 0.0861 1.0000
17.750 1.2969 0.09196 0.08646 -0.0204 0.0782 1.0000
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