E224 (10.17%) (e224-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 200,000 Max Cl/Cd: 63.38 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e224-il-200000-n5.txt Download as CSV file: xf-e224-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E224 (10.17%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5426 0.08156 0.07801 -0.0338 1.0000 0.0106
-10.000 -0.6245 0.05521 0.05146 -0.0528 1.0000 0.0096
-9.750 -0.6530 0.04901 0.04507 -0.0569 1.0000 0.0094
-9.500 -0.6755 0.04545 0.04135 -0.0556 1.0000 0.0094
-9.250 -0.6896 0.04170 0.03730 -0.0539 1.0000 0.0093
-9.000 -0.6950 0.03854 0.03382 -0.0521 1.0000 0.0094
-8.750 -0.6959 0.03553 0.03050 -0.0501 1.0000 0.0095
-8.500 -0.6920 0.03289 0.02754 -0.0480 1.0000 0.0096
-8.250 -0.6842 0.03063 0.02499 -0.0461 1.0000 0.0097
-8.000 -0.6740 0.02858 0.02266 -0.0442 1.0000 0.0099
-7.750 -0.6617 0.02676 0.02058 -0.0424 1.0000 0.0102
-7.500 -0.6476 0.02513 0.01872 -0.0407 1.0000 0.0105
-7.250 -0.6323 0.02364 0.01700 -0.0390 1.0000 0.0108
-7.000 -0.6160 0.02227 0.01544 -0.0373 1.0000 0.0113
-6.750 -0.5874 0.02093 0.01388 -0.0381 0.9973 0.0121
-6.500 -0.5544 0.01991 0.01261 -0.0396 0.9939 0.0133
-6.250 -0.5245 0.01856 0.01119 -0.0408 0.9897 0.0147
-6.000 -0.4922 0.01755 0.01008 -0.0422 0.9856 0.0161
-5.750 -0.4591 0.01664 0.00902 -0.0437 0.9819 0.0180
-5.500 -0.4292 0.01571 0.00799 -0.0445 0.9764 0.0210
-5.250 -0.3958 0.01498 0.00719 -0.0459 0.9721 0.0285
-5.000 -0.3631 0.01429 0.00650 -0.0472 0.9677 0.0410
-4.750 -0.3325 0.01363 0.00596 -0.0482 0.9617 0.0669
-4.500 -0.2981 0.01303 0.00548 -0.0499 0.9576 0.1022
-4.250 -0.2668 0.01250 0.00508 -0.0509 0.9517 0.1433
-4.000 -0.2343 0.01201 0.00474 -0.0522 0.9460 0.1909
-3.750 -0.2002 0.01153 0.00444 -0.0538 0.9414 0.2462
-3.500 -0.1710 0.01117 0.00420 -0.0542 0.9333 0.2915
-3.250 -0.1368 0.01082 0.00395 -0.0556 0.9282 0.3379
-3.000 -0.1081 0.01053 0.00377 -0.0558 0.9192 0.3820
-2.750 -0.0753 0.01024 0.00358 -0.0568 0.9127 0.4267
-2.500 -0.0463 0.00999 0.00344 -0.0570 0.9030 0.4691
-2.250 -0.0165 0.00977 0.00330 -0.0572 0.8936 0.5097
-2.000 0.0141 0.00956 0.00317 -0.0576 0.8847 0.5485
-1.750 0.0422 0.00940 0.00308 -0.0574 0.8735 0.5850
-1.500 0.0701 0.00925 0.00300 -0.0572 0.8621 0.6198
-1.250 0.0979 0.00913 0.00293 -0.0569 0.8506 0.6536
-1.000 0.1252 0.00902 0.00288 -0.0564 0.8386 0.6862
-0.750 0.1520 0.00894 0.00284 -0.0558 0.8260 0.7176
-0.500 0.1783 0.00887 0.00280 -0.0551 0.8127 0.7478
-0.250 0.2042 0.00883 0.00279 -0.0543 0.7989 0.7764
0.000 0.2297 0.00881 0.00278 -0.0534 0.7844 0.8034
0.250 0.2550 0.00880 0.00277 -0.0524 0.7696 0.8297
0.500 0.2802 0.00880 0.00277 -0.0514 0.7542 0.8554
0.750 0.3061 0.00882 0.00278 -0.0506 0.7382 0.8801
1.000 0.3333 0.00885 0.00278 -0.0501 0.7216 0.9040
1.250 0.3630 0.00889 0.00278 -0.0501 0.7043 0.9269
1.500 0.3962 0.00895 0.00277 -0.0510 0.6860 0.9471
1.750 0.4315 0.00902 0.00279 -0.0525 0.6662 0.9661
2.000 0.4677 0.00911 0.00281 -0.0542 0.6453 0.9836
2.250 0.5037 0.00922 0.00284 -0.0560 0.6233 1.0000
2.500 0.5262 0.00938 0.00291 -0.0549 0.6024 1.0000
2.750 0.5493 0.00955 0.00301 -0.0540 0.5808 1.0000
3.000 0.5727 0.00974 0.00312 -0.0531 0.5583 1.0000
3.250 0.5965 0.00994 0.00324 -0.0523 0.5348 1.0000
3.500 0.6203 0.01017 0.00339 -0.0515 0.5107 1.0000
3.750 0.6440 0.01043 0.00357 -0.0507 0.4855 1.0000
4.000 0.6677 0.01070 0.00376 -0.0500 0.4588 1.0000
4.250 0.6914 0.01099 0.00397 -0.0492 0.4313 1.0000
4.500 0.7150 0.01130 0.00420 -0.0485 0.4037 1.0000
4.750 0.7384 0.01165 0.00448 -0.0477 0.3744 1.0000
5.000 0.7614 0.01203 0.00476 -0.0469 0.3442 1.0000
5.250 0.7845 0.01244 0.00508 -0.0462 0.3130 1.0000
5.500 0.8071 0.01289 0.00543 -0.0454 0.2807 1.0000
5.750 0.8297 0.01337 0.00580 -0.0446 0.2501 1.0000
6.000 0.8524 0.01385 0.00624 -0.0438 0.2231 1.0000
6.250 0.8746 0.01438 0.00669 -0.0431 0.1949 1.0000
6.500 0.8956 0.01504 0.00720 -0.0422 0.1610 1.0000
6.750 0.9163 0.01574 0.00774 -0.0413 0.1278 1.0000
7.000 0.9371 0.01643 0.00832 -0.0404 0.1022 1.0000
7.250 0.9580 0.01711 0.00893 -0.0395 0.0836 1.0000
7.500 0.9789 0.01779 0.00962 -0.0385 0.0686 1.0000
7.750 0.9993 0.01851 0.01034 -0.0375 0.0557 1.0000
8.000 1.0187 0.01932 0.01114 -0.0364 0.0444 1.0000
8.250 1.0368 0.02024 0.01204 -0.0351 0.0356 1.0000
8.500 1.0559 0.02102 0.01294 -0.0339 0.0310 1.0000
8.750 1.0726 0.02200 0.01398 -0.0324 0.0276 1.0000
9.000 1.0878 0.02307 0.01518 -0.0307 0.0252 1.0000
9.250 1.1044 0.02397 0.01621 -0.0293 0.0229 1.0000
9.500 1.1196 0.02494 0.01726 -0.0277 0.0209 1.0000
9.750 1.1303 0.02621 0.01861 -0.0256 0.0194 1.0000
10.000 1.1392 0.02748 0.01999 -0.0232 0.0181 1.0000
10.250 1.1507 0.02851 0.02118 -0.0212 0.0166 1.0000
10.500 1.1600 0.02972 0.02251 -0.0191 0.0155 1.0000
10.750 1.1673 0.03110 0.02401 -0.0170 0.0147 1.0000
11.000 1.1725 0.03265 0.02567 -0.0149 0.0139 1.0000
11.250 1.1719 0.03489 0.02800 -0.0126 0.0131 1.0000
11.500 1.1773 0.03666 0.02998 -0.0109 0.0126 1.0000
11.750 1.1821 0.03850 0.03203 -0.0095 0.0119 1.0000
12.000 1.1856 0.04045 0.03416 -0.0083 0.0110 1.0000
12.250 1.1871 0.04265 0.03652 -0.0074 0.0104 1.0000
12.500 1.1869 0.04516 0.03918 -0.0067 0.0101 1.0000
12.750 1.1852 0.04798 0.04214 -0.0064 0.0098 1.0000
13.000 1.1815 0.05117 0.04548 -0.0064 0.0095 1.0000
13.250 1.1754 0.05484 0.04930 -0.0069 0.0092 1.0000
13.500 1.1682 0.05892 0.05355 -0.0078 0.0091 1.0000
13.750 1.1563 0.06391 0.05872 -0.0092 0.0089 1.0000
14.000 1.1455 0.06904 0.06405 -0.0113 0.0088 1.0000
14.250 1.1339 0.07461 0.06984 -0.0139 0.0087 1.0000
14.500 1.1210 0.08071 0.07614 -0.0170 0.0087 1.0000
14.750 1.1061 0.08757 0.08320 -0.0208 0.0087 1.0000
15.000 1.0911 0.09482 0.09063 -0.0251 0.0087 1.0000
15.250 1.0744 0.10289 0.09889 -0.0300 0.0087 1.0000
15.500 1.0574 0.11144 0.10760 -0.0352 0.0087 1.0000
15.750 1.0385 0.12091 0.11723 -0.0410 0.0087 1.0000
16.000 1.0192 0.13096 0.12741 -0.0471 0.0088 1.0000
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