E385 (8.41%) (e385-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E385 (8.41%) (e385-il) Reynolds number: 50,000 Max Cl/Cd: 39.17 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e385-il-50000-n5.txt Download as CSV file: xf-e385-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E385 (8.41%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2768 0.10927 0.10310 -0.0332 1.0000 0.0832
-7.500 -0.2880 0.10856 0.10252 -0.0309 1.0000 0.0845
-7.250 -0.3052 0.10856 0.10267 -0.0281 1.0000 0.0859
-7.000 -0.3120 0.10809 0.10231 -0.0298 0.9949 0.0872
-6.750 -0.2925 0.10481 0.09907 -0.0403 0.9823 0.0887
-6.500 -0.2730 0.09925 0.09347 -0.0365 0.9796 0.0931
-6.250 -0.2527 0.09580 0.08999 -0.0421 0.9699 0.0992
-6.000 -0.2280 0.09363 0.08779 -0.0592 0.9532 0.1030
-5.750 -0.2142 0.08841 0.08261 -0.0536 0.9491 0.1061
-5.500 -0.1945 0.08486 0.07904 -0.0566 0.9406 0.1104
-5.000 -0.1460 0.07740 0.07152 -0.0716 0.9211 0.1200
-4.750 -0.1242 0.07374 0.06782 -0.0741 0.9136 0.1228
-4.500 -0.0651 0.06462 0.05826 -0.0929 0.9054 0.0600
-4.250 -0.0456 0.06131 0.05494 -0.0939 0.8977 0.0557
-4.000 0.0148 0.05374 0.04684 -0.1089 0.8918 0.0468
-3.750 0.0508 0.04965 0.04256 -0.1141 0.8863 0.0455
-3.500 0.0901 0.04554 0.03813 -0.1200 0.8793 0.0444
-3.250 0.1440 0.04084 0.03284 -0.1283 0.8758 0.0448
-3.000 0.1889 0.03736 0.02867 -0.1337 0.8698 0.0463
-2.750 0.2328 0.03436 0.02502 -0.1379 0.8644 0.0476
-2.500 0.2766 0.03175 0.02192 -0.1416 0.8607 0.0490
-2.250 0.3079 0.03024 0.02006 -0.1426 0.8532 0.0512
-2.000 0.3445 0.02879 0.01822 -0.1441 0.8480 0.0564
-1.750 0.3780 0.02770 0.01686 -0.1450 0.8422 0.0656
-1.500 0.4092 0.02684 0.01575 -0.1455 0.8354 0.0786
-1.250 0.4482 0.02577 0.01468 -0.1475 0.8312 0.1287
-1.000 0.4785 0.02486 0.01423 -0.1486 0.8235 0.2435
-0.750 0.5089 0.02344 0.01405 -0.1490 0.8186 0.5778
-0.500 0.5185 0.02287 0.01386 -0.1444 0.8102 1.0000
-0.250 0.5514 0.02307 0.01358 -0.1453 0.8041 1.0000
0.000 0.5804 0.02341 0.01355 -0.1456 0.7973 1.0000
0.250 0.6097 0.02373 0.01356 -0.1460 0.7905 1.0000
0.500 0.6414 0.02396 0.01350 -0.1467 0.7850 1.0000
0.750 0.6662 0.02445 0.01380 -0.1465 0.7770 1.0000
1.000 0.7001 0.02459 0.01373 -0.1474 0.7725 1.0000
1.250 0.7213 0.02524 0.01426 -0.1467 0.7636 1.0000
1.500 0.7536 0.02544 0.01431 -0.1474 0.7587 1.0000
1.750 0.7752 0.02611 0.01489 -0.1468 0.7503 1.0000
2.000 0.8057 0.02638 0.01507 -0.1472 0.7449 1.0000
2.250 0.8284 0.02702 0.01568 -0.1467 0.7372 1.0000
2.500 0.8568 0.02738 0.01600 -0.1469 0.7311 1.0000
2.750 0.8812 0.02796 0.01656 -0.1466 0.7240 1.0000
3.000 0.9069 0.02845 0.01705 -0.1464 0.7171 1.0000
3.250 0.9336 0.02891 0.01755 -0.1463 0.7108 1.0000
3.500 0.9563 0.02956 0.01825 -0.1458 0.7030 1.0000
3.750 0.9847 0.02991 0.01864 -0.1458 0.6971 1.0000
4.000 1.0053 0.03067 0.01947 -0.1450 0.6883 1.0000
4.250 1.0317 0.03110 0.02002 -0.1447 0.6815 1.0000
4.500 1.0544 0.03171 0.02073 -0.1441 0.6731 1.0000
4.750 1.0764 0.03236 0.02149 -0.1433 0.6645 1.0000
5.000 1.1050 0.03257 0.02181 -0.1431 0.6572 1.0000
5.250 1.1232 0.03339 0.02284 -0.1419 0.6468 1.0000
5.500 1.1588 0.03309 0.02268 -0.1422 0.6406 1.0000
5.750 1.1745 0.03398 0.02374 -0.1406 0.6289 1.0000
6.000 1.1940 0.03459 0.02454 -0.1393 0.6178 1.0000
6.250 1.2213 0.03463 0.02482 -0.1386 0.6079 1.0000
6.500 1.2512 0.03440 0.02480 -0.1380 0.5975 1.0000
6.750 1.2708 0.03477 0.02539 -0.1364 0.5842 1.0000
7.000 1.2919 0.03497 0.02587 -0.1349 0.5704 1.0000
7.250 1.3141 0.03500 0.02614 -0.1333 0.5558 1.0000
7.500 1.3375 0.03482 0.02621 -0.1317 0.5401 1.0000
7.750 1.3532 0.03508 0.02672 -0.1294 0.5218 1.0000
8.000 1.3667 0.03540 0.02728 -0.1267 0.5013 1.0000
8.250 1.3833 0.03541 0.02754 -0.1242 0.4789 1.0000
8.500 1.3956 0.03563 0.02796 -0.1213 0.4531 1.0000
8.750 1.4021 0.03624 0.02870 -0.1179 0.4238 1.0000
9.000 1.4052 0.03722 0.02977 -0.1144 0.3897 1.0000
9.250 1.4080 0.03832 0.03078 -0.1109 0.3486 1.0000
9.500 1.4059 0.04009 0.03233 -0.1076 0.3047 1.0000
9.750 1.3991 0.04260 0.03458 -0.1045 0.2634 1.0000
10.000 1.3892 0.04574 0.03747 -0.1020 0.2256 1.0000
10.250 1.3782 0.04936 0.04086 -0.1001 0.1888 1.0000
10.500 1.3662 0.05337 0.04461 -0.0987 0.1555 1.0000
10.750 1.3556 0.05753 0.04861 -0.0978 0.1244 1.0000
11.000 1.3462 0.06180 0.05270 -0.0971 0.1000 1.0000
11.250 1.3382 0.06607 0.05690 -0.0966 0.0823 1.0000
11.500 1.3312 0.07037 0.06116 -0.0961 0.0696 1.0000
11.750 1.3262 0.07453 0.06535 -0.0957 0.0604 1.0000
12.000 1.3215 0.07870 0.06952 -0.0954 0.0549 1.0000
12.250 1.3219 0.08227 0.07329 -0.0947 0.0497 1.0000
12.500 1.3215 0.08596 0.07703 -0.0944 0.0463 1.0000
12.750 1.3264 0.08906 0.08034 -0.0936 0.0428 1.0000
13.000 1.3315 0.09219 0.08371 -0.0931 0.0396 1.0000
13.250 1.3344 0.09556 0.08720 -0.0930 0.0372 1.0000
13.500 1.3415 0.09853 0.09028 -0.0923 0.0352 1.0000
13.750 1.3507 0.10166 0.09386 -0.0915 0.0339 1.0000
14.000 1.3543 0.10575 0.09832 -0.0916 0.0330 1.0000
14.250 1.3527 0.11063 0.10355 -0.0925 0.0324 1.0000
14.500 1.3468 0.11622 0.10946 -0.0943 0.0321 1.0000
14.750 1.3376 0.12256 0.11610 -0.0969 0.0319 1.0000
15.000 1.3253 0.12973 0.12356 -0.1005 0.0318 1.0000
15.250 1.3109 0.13773 0.13181 -0.1051 0.0319 1.0000
15.500 1.2950 0.14657 0.14088 -0.1106 0.0321 1.0000
15.750 1.2781 0.15650 0.15100 -0.1173 0.0325 1.0000
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Polar data table (+)
Polar graphs
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