E224 (10.17%) (e224-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: E224 (10.17%) (e224-il) Reynolds number: 100,000 Max Cl/Cd: 51.19 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e224-il-100000.txt Download as CSV file: xf-e224-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3753 0.12683 0.12193 -0.0189 1.0000 0.0997
-11.500 -0.3942 0.12482 0.11997 -0.0225 1.0000 0.1024
-11.250 -0.4149 0.12226 0.11748 -0.0266 1.0000 0.1030
-11.000 -0.3737 0.11618 0.11134 -0.0220 1.0000 0.1069
-10.750 -0.3694 0.11281 0.10798 -0.0224 1.0000 0.1108
-10.500 -0.3826 0.10955 0.10478 -0.0252 1.0000 0.1155
-10.250 -0.4124 0.10645 0.10178 -0.0303 1.0000 0.1167
-10.000 -0.3757 0.10121 0.09649 -0.0259 1.0000 0.1201
-9.750 -0.3702 0.09767 0.09296 -0.0259 1.0000 0.1237
-9.500 -0.3884 0.09394 0.08931 -0.0291 1.0000 0.1295
-9.250 -0.4036 0.08917 0.08464 -0.0318 1.0000 0.1314
-9.000 -0.3826 0.08528 0.08071 -0.0292 1.0000 0.1341
-8.750 -0.3795 0.08165 0.07711 -0.0291 1.0000 0.1385
-8.500 -0.4751 0.08678 0.08203 -0.0288 1.0000 0.1348
-8.250 -0.4754 0.08341 0.07872 -0.0293 1.0000 0.1380
-7.500 -0.5704 0.05509 0.05009 -0.0470 1.0000 0.0728
-7.250 -0.5831 0.04739 0.04178 -0.0463 1.0000 0.0605
-7.000 -0.5803 0.04277 0.03685 -0.0448 1.0000 0.0573
-6.750 -0.5792 0.03698 0.03004 -0.0426 1.0000 0.0523
-6.500 -0.5649 0.03442 0.02693 -0.0406 1.0000 0.0512
-6.250 -0.5496 0.03152 0.02363 -0.0390 1.0000 0.0512
-6.000 -0.5330 0.02846 0.02030 -0.0377 1.0000 0.0527
-5.750 -0.5148 0.02682 0.01856 -0.0364 1.0000 0.0567
-5.500 -0.4945 0.02510 0.01652 -0.0349 1.0000 0.0605
-5.250 -0.4731 0.02311 0.01425 -0.0334 1.0000 0.0642
-5.000 -0.4529 0.02169 0.01286 -0.0322 1.0000 0.0731
-4.750 -0.4324 0.02024 0.01145 -0.0310 1.0000 0.0856
-4.500 -0.4122 0.01891 0.01022 -0.0298 1.0000 0.1085
-4.250 -0.3915 0.01754 0.00912 -0.0288 1.0000 0.1593
-4.000 -0.3714 0.01638 0.00846 -0.0281 1.0000 0.2423
-3.750 -0.3515 0.01571 0.00818 -0.0272 1.0000 0.3264
-3.500 -0.3317 0.01528 0.00803 -0.0261 1.0000 0.4017
-3.250 -0.3124 0.01498 0.00794 -0.0247 1.0000 0.4683
-3.000 -0.2935 0.01477 0.00793 -0.0232 1.0000 0.5308
-2.750 -0.2754 0.01464 0.00798 -0.0214 1.0000 0.5899
-2.500 -0.2582 0.01457 0.00808 -0.0193 1.0000 0.6461
-2.250 -0.2427 0.01456 0.00821 -0.0169 1.0000 0.7006
-2.000 -0.2289 0.01459 0.00836 -0.0140 1.0000 0.7553
-1.750 -0.2166 0.01466 0.00853 -0.0107 1.0000 0.8113
-1.500 -0.1818 0.01494 0.00889 -0.0113 0.9904 0.8817
-1.250 -0.1158 0.01524 0.00908 -0.0184 0.9844 0.9614
-1.000 -0.0500 0.01539 0.00900 -0.0271 0.9765 1.0000
-0.750 -0.0030 0.01560 0.00899 -0.0321 0.9658 1.0000
-0.500 0.0474 0.01583 0.00905 -0.0373 0.9564 1.0000
-0.250 0.0898 0.01595 0.00903 -0.0408 0.9444 1.0000
0.000 0.1323 0.01605 0.00903 -0.0442 0.9326 1.0000
0.250 0.1769 0.01612 0.00902 -0.0477 0.9215 1.0000
0.500 0.2321 0.01606 0.00891 -0.0529 0.9136 1.0000
0.750 0.2747 0.01598 0.00880 -0.0558 0.9013 1.0000
1.000 0.3169 0.01586 0.00867 -0.0584 0.8891 1.0000
1.250 0.3578 0.01570 0.00851 -0.0605 0.8768 1.0000
1.500 0.3973 0.01549 0.00831 -0.0622 0.8641 1.0000
1.750 0.4338 0.01529 0.00812 -0.0632 0.8504 1.0000
2.000 0.4668 0.01511 0.00797 -0.0635 0.8353 1.0000
2.250 0.4975 0.01496 0.00782 -0.0633 0.8192 1.0000
2.500 0.5270 0.01482 0.00768 -0.0628 0.8023 1.0000
2.750 0.5561 0.01469 0.00757 -0.0621 0.7851 1.0000
3.000 0.5815 0.01467 0.00755 -0.0610 0.7653 1.0000
3.250 0.6073 0.01465 0.00753 -0.0598 0.7447 1.0000
3.500 0.6336 0.01465 0.00750 -0.0587 0.7239 1.0000
3.750 0.6581 0.01471 0.00758 -0.0574 0.7006 1.0000
4.000 0.6826 0.01480 0.00765 -0.0561 0.6765 1.0000
4.250 0.7074 0.01490 0.00771 -0.0549 0.6518 1.0000
4.500 0.7316 0.01505 0.00781 -0.0536 0.6253 1.0000
4.750 0.7549 0.01524 0.00799 -0.0522 0.5968 1.0000
5.000 0.7778 0.01547 0.00818 -0.0508 0.5670 1.0000
5.250 0.7997 0.01575 0.00843 -0.0493 0.5345 1.0000
5.500 0.8214 0.01608 0.00871 -0.0477 0.5007 1.0000
5.750 0.8426 0.01646 0.00901 -0.0462 0.4658 1.0000
6.000 0.8626 0.01690 0.00940 -0.0446 0.4272 1.0000
6.250 0.8819 0.01744 0.00983 -0.0429 0.3873 1.0000
6.500 0.9003 0.01808 0.01035 -0.0411 0.3457 1.0000
6.750 0.9176 0.01885 0.01100 -0.0394 0.3027 1.0000
7.000 0.9337 0.01977 0.01173 -0.0375 0.2587 1.0000
7.250 0.9487 0.02085 0.01260 -0.0356 0.2156 1.0000
7.500 0.9629 0.02206 0.01359 -0.0337 0.1758 1.0000
7.750 0.9765 0.02343 0.01476 -0.0318 0.1420 1.0000
8.000 0.9904 0.02507 0.01623 -0.0299 0.1148 1.0000
8.250 1.0056 0.02684 0.01795 -0.0280 0.0937 1.0000
8.500 1.0239 0.02882 0.01994 -0.0266 0.0805 1.0000
8.750 1.0451 0.03108 0.02216 -0.0257 0.0716 1.0000
9.000 1.0641 0.03281 0.02396 -0.0246 0.0640 1.0000
9.250 1.0875 0.03594 0.02730 -0.0240 0.0598 1.0000
9.500 1.1051 0.03831 0.03003 -0.0225 0.0560 1.0000
9.750 1.1213 0.04049 0.03227 -0.0214 0.0518 1.0000
10.000 1.1351 0.04513 0.03718 -0.0204 0.0499 1.0000
10.250 1.1396 0.04829 0.04086 -0.0178 0.0493 1.0000
10.500 1.1386 0.05165 0.04472 -0.0150 0.0486 1.0000
10.750 1.1324 0.05510 0.04864 -0.0121 0.0480 1.0000
11.000 1.1206 0.05847 0.05238 -0.0091 0.0475 1.0000
11.250 1.1041 0.06184 0.05603 -0.0060 0.0474 1.0000
11.500 1.0853 0.06560 0.06004 -0.0040 0.0475 1.0000
11.750 1.0635 0.06972 0.06440 -0.0032 0.0475 1.0000
12.000 1.0417 0.07457 0.06945 -0.0037 0.0479 1.0000
12.250 1.0198 0.08022 0.07522 -0.0055 0.0485 1.0000
12.500 0.9987 0.08651 0.08164 -0.0083 0.0491 1.0000
12.750 0.9780 0.09357 0.08880 -0.0120 0.0496 1.0000
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Polar data table (+)
Polar graphs
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