E220 (11.48%) (e220-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 200,000 Max Cl/Cd: 76.03 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e220-il-200000.txt Download as CSV file: xf-e220-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: E220 (11.48%)
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3563 0.10925 0.10641 -0.0161 1.0000 0.0464
-10.500 -0.3508 0.10541 0.10259 -0.0180 1.0000 0.0479
-10.250 -0.4606 0.10604 0.10290 -0.0170 1.0000 0.0445
-10.000 -0.4503 0.10311 0.09998 -0.0170 1.0000 0.0458
-9.750 -0.4446 0.09963 0.09655 -0.0185 1.0000 0.0471
-9.500 -0.4412 0.09578 0.09274 -0.0207 1.0000 0.0487
-9.250 -0.4398 0.09157 0.08859 -0.0237 1.0000 0.0504
-9.000 -0.4422 0.08655 0.08364 -0.0287 1.0000 0.0524
-8.750 -0.3882 0.06879 0.06596 -0.0406 0.8921 0.0562
-8.500 -0.3799 0.06662 0.06374 -0.0382 0.8815 0.0574
-8.250 -0.3898 0.06214 0.05923 -0.0404 0.8722 0.0580
-8.000 -0.4066 0.05715 0.05419 -0.0435 0.8629 0.0585
-7.750 -0.4209 0.05336 0.05031 -0.0433 0.8549 0.0591
-7.500 -0.4278 0.04926 0.04611 -0.0435 0.8475 0.0603
-7.250 -0.4335 0.04507 0.04176 -0.0433 0.8414 0.0622
-7.000 -0.4647 0.05177 0.04794 -0.0456 0.8491 0.0633
-6.750 -0.4723 0.04761 0.04313 -0.0436 0.8421 0.0691
-6.500 -0.4557 0.04454 0.04010 -0.0433 0.8353 0.0709
-6.250 -0.4545 0.03352 0.02739 -0.0369 0.8302 0.0327
-6.000 -0.4394 0.02908 0.02268 -0.0355 0.8247 0.0306
-5.750 -0.4204 0.02624 0.01938 -0.0338 0.8191 0.0299
-5.500 -0.3990 0.02407 0.01679 -0.0323 0.8147 0.0300
-5.250 -0.3742 0.02295 0.01535 -0.0315 0.8094 0.0318
-5.000 -0.3496 0.02115 0.01325 -0.0306 0.8043 0.0332
-4.750 -0.3253 0.01939 0.01138 -0.0298 0.8004 0.0349
-4.500 -0.2999 0.01834 0.01030 -0.0292 0.7957 0.0375
-4.250 -0.2747 0.01756 0.00942 -0.0285 0.7909 0.0419
-4.000 -0.2525 0.01660 0.00846 -0.0274 0.7868 0.0499
-3.750 -0.2297 0.01579 0.00763 -0.0263 0.7827 0.0630
-3.500 -0.2078 0.01486 0.00692 -0.0253 0.7780 0.1060
-3.250 -0.1881 0.01387 0.00649 -0.0241 0.7739 0.2179
-3.000 -0.1688 0.01316 0.00625 -0.0226 0.7706 0.3423
-2.750 -0.1508 0.01247 0.00616 -0.0211 0.7657 0.4827
-2.500 -0.1359 0.01168 0.00613 -0.0182 0.7616 0.6622
-2.250 -0.0569 0.01140 0.00639 -0.0270 0.7590 0.8758
-2.000 -0.0050 0.01183 0.00662 -0.0308 0.7562 0.9190
-1.750 0.0416 0.01229 0.00695 -0.0340 0.7521 0.9459
-1.500 0.0938 0.01258 0.00707 -0.0387 0.7481 0.9638
-1.250 0.1466 0.01271 0.00703 -0.0436 0.7446 0.9786
-1.000 0.2012 0.01266 0.00681 -0.0492 0.7417 0.9913
-0.750 0.2507 0.01251 0.00658 -0.0542 0.7371 1.0000
-0.500 0.2734 0.01251 0.00651 -0.0536 0.7324 1.0000
-0.250 0.2959 0.01252 0.00643 -0.0528 0.7287 1.0000
0.000 0.3192 0.01258 0.00644 -0.0523 0.7245 1.0000
0.250 0.3431 0.01264 0.00647 -0.0519 0.7192 1.0000
0.500 0.3664 0.01266 0.00642 -0.0512 0.7150 1.0000
0.750 0.3901 0.01272 0.00644 -0.0505 0.7108 1.0000
1.000 0.4144 0.01281 0.00652 -0.0502 0.7048 1.0000
1.250 0.4382 0.01283 0.00649 -0.0494 0.7003 1.0000
1.500 0.4623 0.01291 0.00654 -0.0488 0.6958 1.0000
1.750 0.4867 0.01300 0.00666 -0.0484 0.6896 1.0000
2.000 0.5107 0.01300 0.00661 -0.0476 0.6850 1.0000
2.250 0.5349 0.01310 0.00673 -0.0470 0.6791 1.0000
2.500 0.5592 0.01313 0.00676 -0.0464 0.6729 1.0000
2.750 0.5835 0.01311 0.00670 -0.0454 0.6686 1.0000
3.000 0.6077 0.01323 0.00690 -0.0450 0.6608 1.0000
3.250 0.6322 0.01318 0.00681 -0.0441 0.6555 1.0000
3.500 0.6563 0.01326 0.00696 -0.0435 0.6478 1.0000
3.750 0.6810 0.01318 0.00688 -0.0427 0.6414 1.0000
4.000 0.7051 0.01323 0.00699 -0.0420 0.6333 1.0000
4.250 0.7299 0.01312 0.00686 -0.0411 0.6265 1.0000
4.500 0.7539 0.01313 0.00697 -0.0404 0.6171 1.0000
4.750 0.7788 0.01301 0.00684 -0.0395 0.6092 1.0000
5.000 0.8029 0.01293 0.00682 -0.0386 0.5988 1.0000
5.250 0.8270 0.01286 0.00683 -0.0378 0.5874 1.0000
5.500 0.8511 0.01276 0.00681 -0.0369 0.5756 1.0000
5.750 0.8751 0.01267 0.00678 -0.0360 0.5621 1.0000
6.000 0.8988 0.01259 0.00677 -0.0350 0.5461 1.0000
6.250 0.9221 0.01253 0.00673 -0.0340 0.5270 1.0000
6.500 0.9446 0.01257 0.00684 -0.0329 0.5026 1.0000
6.750 0.9663 0.01271 0.00696 -0.0317 0.4736 1.0000
7.000 0.9862 0.01300 0.00716 -0.0303 0.4368 1.0000
7.250 1.0038 0.01352 0.00752 -0.0286 0.3941 1.0000
7.500 1.0180 0.01428 0.00806 -0.0266 0.3460 1.0000
7.750 1.0292 0.01523 0.00877 -0.0242 0.2967 1.0000
8.000 1.0390 0.01623 0.00954 -0.0218 0.2503 1.0000
8.250 1.0473 0.01725 0.01037 -0.0191 0.2115 1.0000
8.500 1.0550 0.01825 0.01123 -0.0164 0.1776 1.0000
8.750 1.0605 0.01930 0.01213 -0.0134 0.1488 1.0000
9.000 1.0638 0.02039 0.01310 -0.0101 0.1243 1.0000
9.250 1.0623 0.02153 0.01412 -0.0060 0.1050 1.0000
9.500 1.0572 0.02275 0.01525 -0.0017 0.0905 1.0000
9.750 1.0541 0.02420 0.01667 0.0017 0.0754 1.0000
10.000 1.0508 0.02591 0.01832 0.0047 0.0643 1.0000
10.250 1.0499 0.02765 0.02004 0.0072 0.0548 1.0000
10.500 1.0531 0.02924 0.02169 0.0092 0.0480 1.0000
10.750 1.0520 0.03124 0.02365 0.0114 0.0436 1.0000
11.000 1.0568 0.03294 0.02544 0.0133 0.0405 1.0000
11.250 1.0636 0.03447 0.02705 0.0147 0.0370 1.0000
11.500 1.0679 0.03625 0.02882 0.0162 0.0342 1.0000
11.750 1.0759 0.03813 0.03075 0.0180 0.0321 1.0000
12.000 1.0861 0.03969 0.03246 0.0194 0.0304 1.0000
12.250 1.0943 0.04137 0.03426 0.0206 0.0285 1.0000
12.500 1.1009 0.04309 0.03607 0.0215 0.0268 1.0000
12.750 1.1126 0.04586 0.03886 0.0233 0.0245 1.0000
13.000 1.1178 0.04799 0.04121 0.0243 0.0240 1.0000
13.250 1.1205 0.05049 0.04395 0.0253 0.0233 1.0000
13.500 1.1219 0.05330 0.04700 0.0263 0.0229 1.0000
13.750 1.1189 0.05649 0.05044 0.0270 0.0224 1.0000
14.000 1.1125 0.06002 0.05422 0.0274 0.0219 1.0000
14.250 1.1046 0.06370 0.05811 0.0275 0.0215 1.0000
14.500 1.0973 0.06710 0.06168 0.0272 0.0208 1.0000
14.750 1.0848 0.07158 0.06639 0.0266 0.0208 1.0000
15.000 1.0760 0.07550 0.07043 0.0257 0.0202 1.0000
15.250 1.0649 0.07995 0.07504 0.0243 0.0198 1.0000
15.500 1.0533 0.08471 0.07992 0.0225 0.0194 1.0000
15.750 1.0150 0.09478 0.09042 0.0181 0.0206 1.0000
16.000 0.9834 0.10448 0.10038 0.0129 0.0214 1.0000
16.250 0.9663 0.11183 0.10787 0.0086 0.0208 1.0000
16.500 0.9228 0.12610 0.12234 0.0004 0.0233 1.0000
16.750 0.8943 0.13809 0.13444 -0.0068 0.0237 1.0000
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Polar data table (+)
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