E212 (10.55%) (e212-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E212 (10.55%) (e212-il) Reynolds number: 200,000 Max Cl/Cd: 81.74 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e212-il-200000.txt Download as CSV file: xf-e212-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E212 (10.55%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4461 0.09422 0.09072 -0.0382 1.0000 0.0644
-9.000 -0.4382 0.09241 0.08893 -0.0364 1.0000 0.0658
-8.750 -0.4383 0.08971 0.08627 -0.0359 1.0000 0.0671
-8.500 -0.4425 0.08672 0.08333 -0.0358 1.0000 0.0687
-8.250 -0.4527 0.08335 0.08003 -0.0359 1.0000 0.0705
-8.000 -0.4702 0.07993 0.07670 -0.0360 1.0000 0.0720
-7.250 -0.5765 0.04210 0.03772 -0.0599 1.0000 0.0395
-7.000 -0.5640 0.03207 0.02649 -0.0638 1.0000 0.0331
-6.750 -0.5413 0.03069 0.02471 -0.0635 1.0000 0.0321
-6.500 -0.5177 0.02736 0.02102 -0.0643 1.0000 0.0316
-6.250 -0.4925 0.02495 0.01824 -0.0648 1.0000 0.0315
-6.000 -0.4671 0.02318 0.01620 -0.0649 1.0000 0.0317
-5.750 -0.4420 0.02184 0.01465 -0.0648 1.0000 0.0320
-5.500 -0.4161 0.01983 0.01255 -0.0650 1.0000 0.0331
-5.250 -0.3912 0.01880 0.01152 -0.0651 1.0000 0.0348
-5.000 -0.3658 0.01824 0.01089 -0.0651 0.9998 0.0382
-4.750 -0.3260 0.01731 0.00988 -0.0679 0.9968 0.0416
-4.500 -0.2854 0.01648 0.00903 -0.0709 0.9939 0.0495
-4.250 -0.2448 0.01500 0.00795 -0.0743 0.9910 0.1227
-4.000 -0.2051 0.01465 0.00781 -0.0773 0.9870 0.1875
-3.750 -0.1653 0.01444 0.00778 -0.0802 0.9832 0.2437
-3.500 -0.1283 0.01424 0.00773 -0.0825 0.9776 0.2986
-3.250 -0.0870 0.01414 0.00773 -0.0855 0.9738 0.3462
-3.000 -0.0515 0.01400 0.00763 -0.0872 0.9675 0.3856
-2.750 -0.0118 0.01387 0.00759 -0.0897 0.9628 0.4251
-2.500 0.0262 0.01376 0.00752 -0.0918 0.9576 0.4622
-2.250 0.0627 0.01359 0.00743 -0.0935 0.9513 0.4956
-2.000 0.1052 0.01342 0.00734 -0.0964 0.9477 0.5299
-1.750 0.1371 0.01326 0.00724 -0.0971 0.9395 0.5602
-1.500 0.1783 0.01304 0.00709 -0.0995 0.9351 0.5920
-1.250 0.2121 0.01285 0.00698 -0.1005 0.9277 0.6214
-1.000 0.2512 0.01259 0.00680 -0.1024 0.9224 0.6510
-0.750 0.2947 0.01226 0.00654 -0.1051 0.9194 0.6804
-0.500 0.3246 0.01206 0.00641 -0.1051 0.9099 0.7067
-0.250 0.3670 0.01168 0.00613 -0.1075 0.9063 0.7337
0.000 0.3997 0.01144 0.00597 -0.1079 0.8977 0.7592
0.250 0.4393 0.01109 0.00569 -0.1096 0.8920 0.7857
0.500 0.4694 0.01084 0.00552 -0.1094 0.8818 0.8098
0.750 0.5047 0.01052 0.00526 -0.1101 0.8737 0.8345
1.250 0.5578 0.01008 0.00491 -0.1080 0.8482 0.8861
1.500 0.5806 0.00986 0.00472 -0.1061 0.8337 0.9161
1.750 0.6078 0.00961 0.00448 -0.1052 0.8183 0.9548
2.000 0.6490 0.00947 0.00431 -0.1078 0.8015 1.0000
2.250 0.6814 0.00952 0.00429 -0.1087 0.7819 1.0000
2.500 0.7126 0.00960 0.00430 -0.1093 0.7613 1.0000
2.750 0.7435 0.00972 0.00430 -0.1098 0.7404 1.0000
3.000 0.7713 0.00987 0.00440 -0.1097 0.7169 1.0000
3.250 0.7993 0.01005 0.00448 -0.1095 0.6936 1.0000
3.500 0.8258 0.01025 0.00460 -0.1091 0.6686 1.0000
3.750 0.8516 0.01048 0.00476 -0.1085 0.6427 1.0000
4.000 0.8769 0.01074 0.00493 -0.1079 0.6161 1.0000
4.250 0.9016 0.01103 0.00511 -0.1071 0.5886 1.0000
4.500 0.9256 0.01135 0.00533 -0.1063 0.5600 1.0000
4.750 0.9492 0.01168 0.00559 -0.1053 0.5308 1.0000
5.000 0.9723 0.01205 0.00587 -0.1043 0.5006 1.0000
5.250 0.9948 0.01245 0.00617 -0.1033 0.4696 1.0000
5.500 1.0167 0.01288 0.00651 -0.1021 0.4365 1.0000
5.750 1.0381 0.01334 0.00688 -0.1009 0.4021 1.0000
6.000 1.0591 0.01386 0.00728 -0.0997 0.3679 1.0000
6.250 1.0793 0.01444 0.00772 -0.0984 0.3324 1.0000
6.500 1.0987 0.01507 0.00822 -0.0970 0.2927 1.0000
6.750 1.1175 0.01579 0.00875 -0.0955 0.2511 1.0000
7.000 1.1358 0.01657 0.00934 -0.0941 0.2108 1.0000
7.250 1.1541 0.01740 0.00999 -0.0927 0.1753 1.0000
7.500 1.1721 0.01826 0.01071 -0.0913 0.1438 1.0000
7.750 1.1901 0.01916 0.01148 -0.0899 0.1148 1.0000
8.000 1.2064 0.02021 0.01237 -0.0883 0.0829 1.0000
8.250 1.2155 0.02199 0.01386 -0.0855 0.0478 1.0000
8.500 1.2253 0.02355 0.01539 -0.0826 0.0373 1.0000
8.750 1.2335 0.02502 0.01693 -0.0795 0.0335 1.0000
9.000 1.2445 0.02627 0.01826 -0.0769 0.0310 1.0000
9.250 1.2540 0.02764 0.01970 -0.0743 0.0290 1.0000
9.500 1.2600 0.02963 0.02170 -0.0715 0.0274 1.0000
9.750 1.2734 0.03087 0.02308 -0.0695 0.0261 1.0000
10.000 1.2859 0.03236 0.02469 -0.0675 0.0249 1.0000
10.250 1.2987 0.03403 0.02647 -0.0657 0.0241 1.0000
10.500 1.3121 0.03582 0.02836 -0.0640 0.0234 1.0000
10.750 1.3258 0.03774 0.03039 -0.0625 0.0228 1.0000
11.000 1.3404 0.03994 0.03272 -0.0613 0.0224 1.0000
11.250 1.3553 0.04255 0.03549 -0.0601 0.0220 1.0000
11.500 1.3684 0.04561 0.03876 -0.0589 0.0218 1.0000
11.750 1.3756 0.04875 0.04216 -0.0572 0.0217 1.0000
12.000 1.3772 0.05188 0.04557 -0.0550 0.0217 1.0000
12.250 1.3743 0.05496 0.04893 -0.0527 0.0217 1.0000
12.500 1.3673 0.05819 0.05245 -0.0505 0.0218 1.0000
12.750 1.3567 0.06174 0.05630 -0.0487 0.0220 1.0000
13.000 1.3427 0.06579 0.06066 -0.0474 0.0221 1.0000
13.250 1.3254 0.07046 0.06563 -0.0468 0.0223 1.0000
13.500 1.3038 0.07603 0.07153 -0.0473 0.0225 1.0000
13.750 1.2660 0.08421 0.08015 -0.0500 0.0231 1.0000
14.000 1.2293 0.09355 0.08985 -0.0546 0.0237 1.0000
14.250 1.1960 0.10354 0.10012 -0.0606 0.0242 1.0000
14.500 1.1635 0.11472 0.11152 -0.0682 0.0246 1.0000
14.750 1.1286 0.12809 0.12509 -0.0778 0.0251 1.0000
15.000 1.0847 0.14654 0.14366 -0.0907 0.0260 1.0000
15.250 1.0606 0.16035 0.15748 -0.0989 0.0270 1.0000
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Polar data table (+)
Polar graphs
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