E220 (11.48%) (e220-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 50,000 Max Cl/Cd: 31.81 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e220-il-50000.txt Download as CSV file: xf-e220-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4231 0.11186 0.10570 -0.0104 1.0000 0.2404
-9.250 -0.4247 0.10943 0.10335 -0.0115 1.0000 0.2524
-9.000 -0.4145 0.10561 0.09955 -0.0115 1.0000 0.2665
-8.750 -0.4047 0.10185 0.09585 -0.0116 1.0000 0.2803
-8.500 -0.3959 0.09821 0.09226 -0.0117 1.0000 0.2939
-8.250 -0.3875 0.09463 0.08875 -0.0120 1.0000 0.3063
-8.000 -0.3824 0.09127 0.08547 -0.0123 1.0000 0.3200
-7.750 -0.3777 0.08807 0.08236 -0.0126 1.0000 0.3343
-7.500 -0.3740 0.08488 0.07927 -0.0127 1.0000 0.3494
-7.250 -0.3711 0.08198 0.07647 -0.0125 1.0000 0.3648
-5.500 -0.5760 0.05656 0.05026 -0.0154 1.0000 0.1348
-5.250 -0.5745 0.05213 0.04514 -0.0135 1.0000 0.1219
-5.000 -0.5654 0.04884 0.04169 -0.0116 1.0000 0.1193
-4.750 -0.5558 0.04544 0.03786 -0.0097 1.0000 0.1149
-4.500 -0.5440 0.04236 0.03366 -0.0070 1.0000 0.1088
-4.250 -0.5278 0.03966 0.03051 -0.0054 1.0000 0.1084
-4.000 -0.5109 0.03722 0.02791 -0.0041 1.0000 0.1113
-3.750 -0.4930 0.03549 0.02593 -0.0026 1.0000 0.1176
-3.500 -0.4724 0.03369 0.02350 -0.0010 1.0000 0.1224
-3.250 -0.4519 0.03199 0.02179 0.0000 1.0000 0.1309
-3.000 -0.4304 0.03056 0.02020 0.0012 1.0000 0.1470
-2.750 -0.2290 0.02472 0.01820 -0.0234 1.0000 1.0000
-2.500 -0.2241 0.02467 0.01765 -0.0211 1.0000 1.0000
-2.250 -0.1996 0.02495 0.01738 -0.0221 0.9956 1.0000
-2.000 -0.1724 0.02532 0.01726 -0.0235 0.9899 1.0000
-1.750 -0.1419 0.02586 0.01738 -0.0254 0.9840 1.0000
-1.500 -0.1190 0.02628 0.01746 -0.0259 0.9787 1.0000
-1.250 -0.0913 0.02686 0.01769 -0.0272 0.9730 1.0000
-1.000 -0.0675 0.02742 0.01797 -0.0278 0.9676 1.0000
-0.750 -0.0446 0.02799 0.01830 -0.0282 0.9620 1.0000
-0.500 -0.0156 0.02875 0.01881 -0.0297 0.9561 1.0000
-0.250 0.0017 0.02929 0.01915 -0.0291 0.9507 1.0000
0.000 0.0309 0.03011 0.01977 -0.0306 0.9445 1.0000
0.250 0.0486 0.03076 0.02026 -0.0301 0.9389 1.0000
0.500 0.0720 0.03153 0.02089 -0.0305 0.9325 1.0000
0.750 0.0958 0.03239 0.02160 -0.0311 0.9261 1.0000
1.000 0.1150 0.03315 0.02226 -0.0308 0.9195 1.0000
1.250 0.1412 0.03412 0.02313 -0.0318 0.9122 1.0000
1.500 0.1587 0.03493 0.02386 -0.0312 0.9051 1.0000
1.750 0.1835 0.03596 0.02480 -0.0319 0.8973 1.0000
2.000 0.2040 0.03690 0.02568 -0.0319 0.8892 1.0000
2.250 0.2235 0.03789 0.02663 -0.0318 0.8806 1.0000
2.500 0.2552 0.03913 0.02784 -0.0336 0.8706 1.0000
2.750 0.2681 0.04004 0.02874 -0.0323 0.8613 1.0000
3.000 0.2886 0.04115 0.02983 -0.0323 0.8508 1.0000
3.250 0.3141 0.04236 0.03104 -0.0330 0.8390 1.0000
3.500 0.3413 0.04358 0.03231 -0.0338 0.8262 1.0000
3.750 0.3681 0.04481 0.03357 -0.0345 0.8128 1.0000
4.000 0.3933 0.04601 0.03481 -0.0349 0.7987 1.0000
4.250 0.4150 0.04717 0.03602 -0.0348 0.7838 1.0000
4.500 0.4356 0.04833 0.03724 -0.0344 0.7687 1.0000
4.750 0.4544 0.04948 0.03848 -0.0337 0.7526 1.0000
5.000 0.4740 0.05064 0.03971 -0.0331 0.7359 1.0000
5.250 0.4966 0.05177 0.04093 -0.0328 0.7186 1.0000
5.500 0.5260 0.05278 0.04206 -0.0330 0.7007 1.0000
5.750 0.5617 0.05361 0.04307 -0.0336 0.6825 1.0000
6.000 0.5702 0.05480 0.04434 -0.0316 0.6640 1.0000
6.250 0.5930 0.05566 0.04534 -0.0307 0.6449 1.0000
6.500 0.6341 0.05586 0.04579 -0.0310 0.6261 1.0000
6.750 0.6442 0.05695 0.04699 -0.0290 0.6063 1.0000
7.000 0.6699 0.05733 0.04755 -0.0279 0.5864 1.0000
7.250 0.7153 0.05644 0.04698 -0.0273 0.5668 1.0000
7.500 0.7229 0.05741 0.04807 -0.0249 0.5453 1.0000
7.750 0.7929 0.05367 0.04479 -0.0239 0.5245 1.0000
8.000 0.8057 0.05374 0.04503 -0.0209 0.5014 1.0000
8.250 0.9679 0.03800 0.03024 -0.0185 0.4676 1.0000
8.500 1.0128 0.03403 0.02635 -0.0149 0.4208 1.0000
8.750 1.0395 0.03268 0.02464 -0.0113 0.3659 1.0000
9.000 1.0491 0.03360 0.02520 -0.0076 0.3171 1.0000
9.250 1.0564 0.03514 0.02638 -0.0042 0.2736 1.0000
9.500 1.0625 0.03697 0.02790 -0.0010 0.2364 1.0000
9.750 1.0681 0.03901 0.02974 0.0019 0.2044 1.0000
10.000 1.0761 0.04121 0.03183 0.0044 0.1773 1.0000
10.250 1.0892 0.04371 0.03416 0.0062 0.1538 1.0000
10.500 1.0981 0.04633 0.03688 0.0083 0.1372 1.0000
10.750 1.1112 0.04949 0.04017 0.0099 0.1249 1.0000
11.000 1.1280 0.05288 0.04360 0.0109 0.1149 1.0000
11.250 1.1195 0.05582 0.04699 0.0141 0.1105 1.0000
11.500 1.1408 0.05975 0.05083 0.0143 0.1029 1.0000
11.750 1.1269 0.06312 0.05461 0.0175 0.1021 1.0000
12.000 1.1093 0.06651 0.05831 0.0205 0.1017 1.0000
12.250 1.0897 0.07026 0.06232 0.0226 0.1016 1.0000
12.500 1.0693 0.07438 0.06667 0.0237 0.1018 1.0000
12.750 1.0461 0.07907 0.07155 0.0241 0.1020 1.0000
13.000 1.0238 0.08421 0.07686 0.0237 0.1025 1.0000
13.250 1.0015 0.08994 0.08271 0.0225 0.1029 1.0000
13.500 0.8412 0.11831 0.11115 0.0015 0.1320 1.0000
13.750 0.8424 0.12344 0.11629 0.0008 0.1300 1.0000
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Polar data table (+)
Polar graphs
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