E211 (10.96%) (e211-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E211 (10.96%) (e211-il) Reynolds number: 100,000 Max Cl/Cd: 58.27 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e211-il-100000.txt Download as CSV file: xf-e211-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E211 (10.96%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4261 0.09718 0.09230 -0.0327 1.0000 0.1218
-8.500 -0.4341 0.09430 0.08950 -0.0333 1.0000 0.1270
-8.250 -0.4809 0.09198 0.08740 -0.0369 1.0000 0.1297
-8.000 -0.4644 0.08775 0.08318 -0.0343 1.0000 0.1323
-7.750 -0.4532 0.08518 0.08062 -0.0318 1.0000 0.1359
-7.500 -0.4672 0.08268 0.07822 -0.0307 1.0000 0.1398
-7.250 -0.5205 0.07652 0.07214 -0.0408 1.0000 0.1453
-7.000 -0.4977 0.07459 0.07031 -0.0344 1.0000 0.1480
-6.750 -0.4962 0.07182 0.06757 -0.0332 1.0000 0.1525
-6.250 -0.5214 0.04578 0.04000 -0.0509 1.0000 0.0762
-6.000 -0.5038 0.03892 0.03210 -0.0517 1.0000 0.0622
-5.750 -0.4842 0.03592 0.02864 -0.0515 1.0000 0.0620
-5.500 -0.4629 0.03327 0.02557 -0.0512 1.0000 0.0618
-5.250 -0.4399 0.03115 0.02303 -0.0508 1.0000 0.0612
-5.000 -0.4156 0.02858 0.02011 -0.0506 1.0000 0.0610
-4.750 -0.3910 0.02659 0.01780 -0.0502 1.0000 0.0614
-4.500 -0.3669 0.02438 0.01546 -0.0498 1.0000 0.0630
-4.250 -0.3439 0.02305 0.01412 -0.0492 1.0000 0.0661
-4.000 -0.3212 0.02220 0.01316 -0.0484 1.0000 0.0726
-3.750 -0.2987 0.02109 0.01215 -0.0479 1.0000 0.0808
-3.500 -0.2750 0.02000 0.01116 -0.0474 1.0000 0.0977
-3.250 -0.2475 0.01811 0.00998 -0.0484 1.0000 0.2027
-3.000 -0.2237 0.01664 0.01004 -0.0489 1.0000 0.4605
-2.750 -0.2076 0.01692 0.01062 -0.0467 1.0000 0.5898
-2.500 -0.1927 0.01732 0.01107 -0.0442 1.0000 0.6442
-2.250 -0.1568 0.01801 0.01169 -0.0454 0.9914 0.6958
-2.000 -0.1208 0.01858 0.01222 -0.0464 0.9817 0.7359
-1.750 -0.0843 0.01902 0.01260 -0.0476 0.9723 0.7703
-1.500 -0.0535 0.01918 0.01270 -0.0477 0.9610 0.7996
-1.250 -0.0243 0.01924 0.01272 -0.0476 0.9499 0.8261
-1.000 0.0041 0.01922 0.01267 -0.0472 0.9390 0.8515
-0.750 0.0344 0.01914 0.01252 -0.0472 0.9291 0.8775
-0.500 0.0676 0.01898 0.01232 -0.0477 0.9200 0.9050
-0.250 0.1000 0.01878 0.01210 -0.0484 0.9090 0.9344
0.000 0.1562 0.01867 0.01192 -0.0540 0.9021 0.9640
0.250 0.2204 0.01849 0.01166 -0.0616 0.8945 0.9971
0.500 0.2585 0.01833 0.01141 -0.0647 0.8837 1.0000
0.750 0.3098 0.01802 0.01103 -0.0697 0.8774 1.0000
1.000 0.3474 0.01788 0.01083 -0.0723 0.8660 1.0000
1.250 0.3918 0.01763 0.01054 -0.0758 0.8573 1.0000
1.500 0.4413 0.01728 0.01016 -0.0800 0.8501 1.0000
1.750 0.4816 0.01712 0.01000 -0.0826 0.8394 1.0000
2.000 0.5344 0.01664 0.00952 -0.0869 0.8333 1.0000
2.250 0.5706 0.01655 0.00942 -0.0885 0.8208 1.0000
2.500 0.6077 0.01646 0.00935 -0.0902 0.8085 1.0000
2.750 0.6452 0.01635 0.00926 -0.0918 0.7960 1.0000
3.000 0.6819 0.01627 0.00918 -0.0931 0.7827 1.0000
3.250 0.7165 0.01623 0.00917 -0.0940 0.7682 1.0000
3.500 0.7491 0.01625 0.00920 -0.0945 0.7526 1.0000
3.750 0.7803 0.01631 0.00927 -0.0947 0.7363 1.0000
4.000 0.8106 0.01639 0.00936 -0.0947 0.7194 1.0000
4.250 0.8407 0.01648 0.00946 -0.0946 0.7020 1.0000
4.500 0.8678 0.01663 0.00963 -0.0940 0.6832 1.0000
4.750 0.8929 0.01681 0.00984 -0.0931 0.6630 1.0000
5.000 0.9200 0.01694 0.00999 -0.0924 0.6430 1.0000
5.250 0.9439 0.01713 0.01022 -0.0912 0.6213 1.0000
5.500 0.9685 0.01728 0.01038 -0.0901 0.5987 1.0000
5.750 0.9904 0.01746 0.01062 -0.0885 0.5739 1.0000
6.000 1.0122 0.01763 0.01083 -0.0869 0.5473 1.0000
6.250 1.0320 0.01780 0.01103 -0.0849 0.5170 1.0000
6.500 1.0501 0.01802 0.01125 -0.0826 0.4825 1.0000
6.750 1.0660 0.01833 0.01152 -0.0800 0.4419 1.0000
7.000 1.0793 0.01881 0.01188 -0.0771 0.3929 1.0000
7.250 1.0891 0.01961 0.01245 -0.0738 0.3335 1.0000
7.500 1.0956 0.02082 0.01327 -0.0702 0.2690 1.0000
7.750 1.1008 0.02230 0.01432 -0.0668 0.2120 1.0000
8.000 1.1067 0.02380 0.01548 -0.0638 0.1642 1.0000
8.250 1.1123 0.02545 0.01688 -0.0606 0.1266 1.0000
8.500 1.1133 0.02740 0.01858 -0.0568 0.0947 1.0000
8.750 1.1159 0.02950 0.02053 -0.0531 0.0717 1.0000
9.000 1.1251 0.03163 0.02263 -0.0505 0.0608 1.0000
9.250 1.1435 0.03415 0.02504 -0.0494 0.0544 1.0000
9.500 1.1683 0.03636 0.02744 -0.0488 0.0497 1.0000
9.750 1.1937 0.03893 0.02996 -0.0491 0.0456 1.0000
10.000 1.2178 0.04196 0.03328 -0.0488 0.0431 1.0000
10.250 1.2361 0.04490 0.03659 -0.0476 0.0419 1.0000
10.500 1.2485 0.04816 0.04024 -0.0458 0.0413 1.0000
10.750 1.2534 0.05150 0.04402 -0.0433 0.0410 1.0000
11.000 1.2519 0.05487 0.04777 -0.0402 0.0411 1.0000
11.250 1.2447 0.05835 0.05161 -0.0368 0.0413 1.0000
11.500 1.2336 0.06195 0.05554 -0.0337 0.0416 1.0000
11.750 1.2192 0.06572 0.05961 -0.0310 0.0419 1.0000
12.000 1.2025 0.06976 0.06392 -0.0289 0.0423 1.0000
12.250 1.1838 0.07415 0.06856 -0.0277 0.0426 1.0000
12.500 1.1637 0.07899 0.07363 -0.0275 0.0429 1.0000
12.750 1.1429 0.08433 0.07917 -0.0283 0.0433 1.0000
13.000 1.1217 0.09023 0.08525 -0.0300 0.0437 1.0000
13.250 1.1013 0.09670 0.09187 -0.0325 0.0441 1.0000
13.500 0.9427 0.10106 0.09675 -0.0306 0.0446 1.0000
13.750 0.9029 0.10840 0.10437 -0.0365 0.0455 1.0000
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Polar data table (+)
Polar graphs
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