E64 (8.45%) (e64-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E64 (8.45%) (e64-il) Reynolds number: 200,000 Max Cl/Cd: 81.76 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e64-il-200000-n5.txt Download as CSV file: xf-e64-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E64 (8.45%)
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4122 0.08748 0.08414 -0.0344 1.0000 0.0261
-7.750 -0.4229 0.08517 0.08190 -0.0328 1.0000 0.0262
-7.500 -0.4349 0.08314 0.07994 -0.0307 1.0000 0.0263
-7.250 -0.4261 0.07795 0.07478 -0.0366 0.9970 0.0262
-6.750 -0.3849 0.05932 0.05599 -0.0584 0.9862 0.0137
-6.500 -0.3629 0.05191 0.04841 -0.0676 0.9802 0.0132
-6.250 -0.3364 0.04395 0.04014 -0.0763 0.9751 0.0127
-6.000 -0.3095 0.03641 0.03210 -0.0828 0.9703 0.0122
-5.750 -0.2820 0.03045 0.02551 -0.0866 0.9652 0.0120
-5.500 -0.2494 0.02594 0.02030 -0.0897 0.9623 0.0119
-5.250 -0.2151 0.02285 0.01662 -0.0920 0.9603 0.0121
-5.000 -0.1876 0.02112 0.01445 -0.0923 0.9553 0.0132
-4.750 -0.1558 0.01976 0.01268 -0.0933 0.9518 0.0139
-4.500 -0.1227 0.01808 0.01076 -0.0946 0.9493 0.0142
-4.250 -0.0886 0.01667 0.00921 -0.0961 0.9473 0.0146
-4.000 -0.0603 0.01571 0.00817 -0.0964 0.9425 0.0151
-3.750 -0.0288 0.01493 0.00729 -0.0973 0.9384 0.0158
-3.500 0.0058 0.01424 0.00649 -0.0988 0.9356 0.0170
-3.250 0.0420 0.01367 0.00579 -0.1005 0.9334 0.0190
-3.000 0.0704 0.01320 0.00529 -0.1007 0.9275 0.0239
-2.750 0.1039 0.01261 0.00472 -0.1018 0.9235 0.0408
-2.500 0.1391 0.01187 0.00434 -0.1037 0.9205 0.1287
-2.250 0.1701 0.01126 0.00415 -0.1048 0.9156 0.2403
-2.000 0.2003 0.01070 0.00402 -0.1056 0.9098 0.3660
-1.750 0.2345 0.01030 0.00384 -0.1069 0.9058 0.4512
-1.500 0.2628 0.01003 0.00375 -0.1070 0.8985 0.5231
-1.250 0.2945 0.00973 0.00364 -0.1076 0.8927 0.5948
-1.000 0.3226 0.00948 0.00357 -0.1074 0.8852 0.6637
-0.750 0.3515 0.00925 0.00348 -0.1072 0.8781 0.7288
-0.500 0.3763 0.00908 0.00344 -0.1060 0.8692 0.7886
-0.250 0.4033 0.00887 0.00331 -0.1052 0.8617 0.8494
0.000 0.4283 0.00872 0.00320 -0.1040 0.8511 0.9165
0.250 0.4659 0.00858 0.00303 -0.1058 0.8412 1.0000
0.500 0.4967 0.00858 0.00295 -0.1063 0.8305 1.0000
0.750 0.5271 0.00860 0.00288 -0.1067 0.8190 1.0000
1.000 0.5559 0.00863 0.00284 -0.1068 0.8057 1.0000
1.250 0.5846 0.00868 0.00282 -0.1068 0.7913 1.0000
1.500 0.6129 0.00875 0.00283 -0.1067 0.7755 1.0000
1.750 0.6405 0.00883 0.00285 -0.1065 0.7585 1.0000
2.000 0.6678 0.00893 0.00289 -0.1063 0.7403 1.0000
2.250 0.6950 0.00906 0.00293 -0.1060 0.7207 1.0000
2.500 0.7214 0.00920 0.00302 -0.1055 0.6989 1.0000
3.000 0.7730 0.00957 0.00322 -0.1044 0.6503 1.0000
3.250 0.7980 0.00980 0.00338 -0.1037 0.6234 1.0000
3.500 0.8225 0.01006 0.00355 -0.1030 0.5943 1.0000
3.750 0.8463 0.01036 0.00374 -0.1021 0.5625 1.0000
4.000 0.8694 0.01070 0.00396 -0.1011 0.5280 1.0000
4.250 0.8919 0.01109 0.00423 -0.1000 0.4907 1.0000
4.500 0.9141 0.01151 0.00452 -0.0990 0.4532 1.0000
4.750 0.9358 0.01198 0.00485 -0.0978 0.4150 1.0000
5.000 0.9563 0.01255 0.00523 -0.0966 0.3670 1.0000
5.250 0.9748 0.01329 0.00569 -0.0951 0.3070 1.0000
5.500 0.9935 0.01409 0.00619 -0.0937 0.2487 1.0000
5.750 1.0135 0.01482 0.00671 -0.0925 0.2036 1.0000
6.000 1.0323 0.01569 0.00730 -0.0913 0.1527 1.0000
6.250 1.0521 0.01650 0.00791 -0.0902 0.1145 1.0000
6.500 1.0716 0.01733 0.00860 -0.0890 0.0816 1.0000
6.750 1.0909 0.01820 0.00933 -0.0878 0.0530 1.0000
7.000 1.1092 0.01917 0.01018 -0.0864 0.0306 1.0000
7.250 1.1281 0.02009 0.01110 -0.0850 0.0218 1.0000
7.500 1.1470 0.02097 0.01204 -0.0836 0.0188 1.0000
7.750 1.1662 0.02178 0.01296 -0.0823 0.0168 1.0000
8.000 1.1838 0.02272 0.01401 -0.0808 0.0153 1.0000
8.250 1.1998 0.02379 0.01519 -0.0791 0.0144 1.0000
8.500 1.2155 0.02481 0.01637 -0.0773 0.0139 1.0000
8.750 1.2296 0.02593 0.01763 -0.0753 0.0134 1.0000
9.000 1.2417 0.02711 0.01895 -0.0730 0.0131 1.0000
9.250 1.2528 0.02838 0.02035 -0.0706 0.0127 1.0000
9.500 1.2633 0.02976 0.02185 -0.0683 0.0124 1.0000
9.750 1.2735 0.03123 0.02349 -0.0660 0.0122 1.0000
10.000 1.2834 0.03282 0.02521 -0.0638 0.0120 1.0000
10.250 1.2932 0.03452 0.02707 -0.0616 0.0117 1.0000
10.500 1.3025 0.03632 0.02903 -0.0596 0.0115 1.0000
10.750 1.3107 0.03817 0.03103 -0.0576 0.0113 1.0000
11.000 1.3171 0.04017 0.03319 -0.0557 0.0109 1.0000
11.250 1.3215 0.04258 0.03575 -0.0537 0.0106 1.0000
11.500 1.3225 0.04582 0.03922 -0.0517 0.0103 1.0000
11.750 1.3231 0.04822 0.04187 -0.0498 0.0101 1.0000
12.000 1.3214 0.05105 0.04499 -0.0481 0.0100 1.0000
12.250 1.3170 0.05424 0.04845 -0.0466 0.0100 1.0000
12.500 1.3101 0.05779 0.05227 -0.0455 0.0099 1.0000
12.750 1.3006 0.06175 0.05650 -0.0449 0.0099 1.0000
13.000 1.2892 0.06618 0.06119 -0.0449 0.0099 1.0000
13.250 1.2757 0.07113 0.06640 -0.0457 0.0098 1.0000
13.500 1.2606 0.07669 0.07221 -0.0473 0.0098 1.0000
13.750 1.2443 0.08286 0.07860 -0.0497 0.0098 1.0000
14.000 1.2268 0.08975 0.08572 -0.0531 0.0098 1.0000
14.250 1.2089 0.09732 0.09349 -0.0574 0.0099 1.0000
14.500 1.1903 0.10569 0.10206 -0.0625 0.0099 1.0000
14.750 1.1713 0.11491 0.11145 -0.0685 0.0100 1.0000
15.000 1.1520 0.12496 0.12166 -0.0752 0.0100 1.0000
15.250 1.1322 0.13590 0.13271 -0.0824 0.0101 1.0000
15.500 1.1120 0.14776 0.14468 -0.0900 0.0102 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E64 (8.45%) (e64-il)