EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 654 AIRFOIL (e654-il) Reynolds number: 200,000 Max Cl/Cd: 70.6 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e654-il-200000.txt Download as CSV file: xf-e654-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 654 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0167 0.10312 0.09883 -0.1235 0.8514 0.0524
-11.500 -0.0161 0.09969 0.09538 -0.1255 0.8461 0.0549
-11.250 -0.0455 0.09274 0.08846 -0.1323 0.8414 0.0568
-11.000 -0.0255 0.09099 0.08669 -0.1305 0.8370 0.0576
-10.750 -0.0160 0.08860 0.08429 -0.1308 0.8326 0.0582
-10.500 -0.0059 0.08638 0.08205 -0.1310 0.8287 0.0601
-10.250 -0.0043 0.08306 0.07870 -0.1326 0.8252 0.0616
-10.000 -0.0703 0.07166 0.06738 -0.1455 0.8200 0.0654
-9.750 -0.1079 0.06719 0.06284 -0.1485 0.8147 0.0654
-9.500 -0.0538 0.06537 0.06115 -0.1452 0.8129 0.0670
-9.250 -0.1885 0.04758 0.04269 -0.1483 0.8069 0.0371
-9.000 -0.2121 0.04207 0.03681 -0.1457 0.8029 0.0301
-8.750 -0.2452 0.03658 0.03037 -0.1414 0.7986 0.0266
-8.500 -0.2354 0.03419 0.02775 -0.1402 0.7956 0.0263
-8.250 -0.2229 0.03203 0.02528 -0.1391 0.7928 0.0262
-8.000 -0.2077 0.03003 0.02291 -0.1381 0.7904 0.0262
-7.750 -0.1906 0.02837 0.02091 -0.1370 0.7876 0.0264
-7.500 -0.1723 0.02692 0.01923 -0.1360 0.7844 0.0268
-7.250 -0.1512 0.02570 0.01802 -0.1355 0.7815 0.0278
-7.000 -0.1289 0.02485 0.01710 -0.1349 0.7789 0.0291
-6.750 -0.1062 0.02404 0.01608 -0.1343 0.7765 0.0316
-6.500 -0.0827 0.02335 0.01542 -0.1340 0.7744 0.0344
-6.250 -0.0587 0.02249 0.01444 -0.1335 0.7723 0.0370
-6.000 -0.0383 0.02192 0.01393 -0.1326 0.7696 0.0407
-5.750 -0.0190 0.02143 0.01350 -0.1317 0.7665 0.0462
-5.500 0.0015 0.02091 0.01302 -0.1309 0.7638 0.0542
-5.250 0.0230 0.02032 0.01247 -0.1303 0.7613 0.0665
-5.000 0.0462 0.01980 0.01203 -0.1301 0.7589 0.0857
-4.750 0.0707 0.01918 0.01154 -0.1300 0.7568 0.1156
-4.500 0.0959 0.01853 0.01115 -0.1303 0.7549 0.1680
-4.250 0.1172 0.01812 0.01110 -0.1302 0.7523 0.2458
-4.000 0.1368 0.01780 0.01122 -0.1300 0.7491 0.3397
-3.750 0.1592 0.01746 0.01134 -0.1298 0.7462 0.4502
-3.500 0.1828 0.01735 0.01164 -0.1291 0.7436 0.5548
-3.250 0.2085 0.01757 0.01197 -0.1283 0.7414 0.6193
-3.000 0.2351 0.01790 0.01226 -0.1277 0.7395 0.6564
-2.750 0.2631 0.01828 0.01254 -0.1273 0.7379 0.6842
-2.500 0.2858 0.01885 0.01308 -0.1261 0.7357 0.7029
-2.250 0.2968 0.01971 0.01400 -0.1233 0.7308 0.7170
-2.000 0.3151 0.02027 0.01456 -0.1213 0.7274 0.7302
-1.750 0.3376 0.02067 0.01492 -0.1199 0.7251 0.7433
-1.500 0.3649 0.02090 0.01505 -0.1196 0.7232 0.7565
-1.250 0.3890 0.02111 0.01522 -0.1181 0.7214 0.7659
-1.000 0.4161 0.02130 0.01534 -0.1175 0.7199 0.7767
-0.750 0.4102 0.02268 0.01684 -0.1127 0.7125 0.7864
-0.500 0.4271 0.02306 0.01721 -0.1107 0.7090 0.7954
-0.250 0.4542 0.02318 0.01726 -0.1104 0.7069 0.8060
0.000 0.4787 0.02315 0.01720 -0.1091 0.7052 0.8136
0.250 0.5112 0.02311 0.01707 -0.1098 0.7037 0.8233
0.500 0.5373 0.02307 0.01699 -0.1088 0.7023 0.8297
0.750 0.5137 0.02508 0.01914 -0.1023 0.6911 0.8395
1.000 0.5397 0.02490 0.01893 -0.1014 0.6892 0.8457
1.250 0.5732 0.02465 0.01862 -0.1021 0.6879 0.8525
1.500 0.6090 0.02436 0.01826 -0.1032 0.6867 0.8584
1.750 0.6407 0.02412 0.01798 -0.1035 0.6855 0.8636
2.000 0.6108 0.02636 0.02036 -0.0963 0.6728 0.8729
2.250 0.6440 0.02590 0.01987 -0.0966 0.6715 0.8774
2.500 0.6110 0.02823 0.02229 -0.0890 0.6592 0.8868
2.750 0.6423 0.02789 0.02194 -0.0893 0.6571 0.8915
3.000 0.6808 0.02731 0.02134 -0.0906 0.6560 0.8959
3.250 0.7244 0.02671 0.02070 -0.0929 0.6551 0.9001
3.500 0.7698 0.02604 0.02000 -0.0956 0.6543 0.9039
3.750 0.8080 0.02539 0.01933 -0.0968 0.6533 0.9078
4.000 0.8497 0.02475 0.01867 -0.0987 0.6523 0.9117
4.250 0.8104 0.02681 0.02086 -0.0895 0.6390 0.9231
4.500 0.7946 0.02844 0.02257 -0.0841 0.6289 0.9339
4.750 0.8534 0.02681 0.02091 -0.0878 0.6308 0.9366
5.000 0.9177 0.02531 0.01939 -0.0928 0.6325 0.9388
5.250 0.9888 0.02363 0.01764 -0.0989 0.6348 0.9402
5.500 0.9591 0.02510 0.01926 -0.0908 0.6226 0.9566
5.750 1.0106 0.02411 0.01828 -0.0943 0.6216 0.9613
6.000 1.0625 0.02310 0.01727 -0.0979 0.6203 0.9668
6.250 1.1148 0.02221 0.01637 -0.1018 0.6187 0.9725
6.500 1.1117 0.02333 0.01765 -0.0986 0.6076 1.0000
6.750 1.1663 0.02226 0.01657 -0.1027 0.6056 1.0000
7.000 1.2207 0.02124 0.01553 -0.1069 0.6034 1.0000
7.250 1.2192 0.02207 0.01650 -0.1034 0.5930 1.0000
7.500 1.2714 0.02107 0.01550 -0.1072 0.5895 1.0000
7.750 1.2868 0.02126 0.01577 -0.1059 0.5815 1.0000
8.000 1.3219 0.02077 0.01530 -0.1072 0.5752 1.0000
8.250 1.3479 0.02060 0.01519 -0.1073 0.5678 1.0000
8.500 1.3727 0.02042 0.01504 -0.1071 0.5593 1.0000
8.750 1.3851 0.02070 0.01538 -0.1052 0.5491 1.0000
9.000 1.4218 0.02014 0.01479 -0.1066 0.5405 1.0000
9.250 1.4259 0.02074 0.01545 -0.1036 0.5277 1.0000
9.500 1.4347 0.02131 0.01605 -0.1013 0.5144 1.0000
9.750 1.4464 0.02184 0.01657 -0.0996 0.5002 1.0000
10.000 1.4579 0.02245 0.01717 -0.0978 0.4849 1.0000
10.250 1.4676 0.02322 0.01790 -0.0959 0.4687 1.0000
10.500 1.4755 0.02415 0.01877 -0.0939 0.4515 1.0000
10.750 1.4824 0.02522 0.01977 -0.0919 0.4341 1.0000
11.000 1.4876 0.02646 0.02092 -0.0898 0.4165 1.0000
11.500 1.4923 0.02949 0.02383 -0.0856 0.3820 1.0000
11.750 1.4933 0.03121 0.02550 -0.0835 0.3653 1.0000
12.000 1.4937 0.03303 0.02727 -0.0816 0.3490 1.0000
12.250 1.4941 0.03492 0.02913 -0.0797 0.3332 1.0000
12.500 1.4946 0.03689 0.03104 -0.0780 0.3179 1.0000
13.000 1.4948 0.04112 0.03521 -0.0750 0.2884 1.0000
13.250 1.4953 0.04334 0.03743 -0.0737 0.2741 1.0000
13.500 1.4958 0.04563 0.03971 -0.0725 0.2603 1.0000
13.750 1.4964 0.04798 0.04206 -0.0714 0.2470 1.0000
14.000 1.4972 0.05039 0.04445 -0.0705 0.2343 1.0000
14.250 1.4974 0.05290 0.04693 -0.0696 0.2223 1.0000
14.500 1.4973 0.05551 0.04951 -0.0688 0.2105 1.0000
14.750 1.4983 0.05814 0.05219 -0.0682 0.1987 1.0000
15.000 1.4989 0.06086 0.05492 -0.0677 0.1877 1.0000
15.250 1.4988 0.06368 0.05771 -0.0672 0.1775 1.0000
15.500 1.4980 0.06666 0.06070 -0.0668 0.1674 1.0000
15.750 1.4989 0.06954 0.06365 -0.0666 0.1575 1.0000
16.000 1.4980 0.07265 0.06674 -0.0664 0.1487 1.0000
16.250 1.4971 0.07585 0.06996 -0.0663 0.1400 1.0000
16.500 1.4973 0.07899 0.07316 -0.0664 0.1316 1.0000
16.750 1.4951 0.08237 0.07647 -0.0665 0.1243 1.0000
17.000 1.4953 0.08568 0.07993 -0.0668 0.1166 1.0000
17.250 1.4933 0.08917 0.08340 -0.0671 0.1101 1.0000
17.500 1.4925 0.09269 0.08702 -0.0676 0.1034 1.0000
17.750 1.4909 0.09621 0.09053 -0.0681 0.0976 1.0000
18.000 1.4893 0.09990 0.09433 -0.0688 0.0918 1.0000
18.250 1.4880 0.10344 0.09784 -0.0695 0.0866 1.0000
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Polar data table (+)
Polar graphs
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