E220 (11.48%) (e220-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E220 (11.48%) (e220-il) Reynolds number: 100,000 Max Cl/Cd: 52.22 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e220-il-100000-n5.txt Download as CSV file: xf-e220-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4558 0.09387 0.08942 -0.0229 1.0000 0.0222
-9.500 -0.4585 0.08854 0.08415 -0.0262 1.0000 0.0216
-9.250 -0.4646 0.08230 0.07801 -0.0306 1.0000 0.0210
-9.000 -0.4955 0.06670 0.06240 -0.0445 1.0000 0.0192
-8.750 -0.5068 0.06212 0.05777 -0.0470 0.9755 0.0191
-8.500 -0.5098 0.05719 0.05260 -0.0500 0.9246 0.0190
-8.250 -0.5146 0.05301 0.04812 -0.0502 0.9008 0.0189
-8.000 -0.5201 0.04891 0.04362 -0.0490 0.8838 0.0189
-7.750 -0.5201 0.04541 0.03973 -0.0473 0.8712 0.0188
-7.500 -0.5181 0.04174 0.03552 -0.0452 0.8600 0.0190
-7.250 -0.5112 0.03865 0.03198 -0.0434 0.8504 0.0196
-7.000 -0.4978 0.03691 0.03005 -0.0421 0.8427 0.0207
-6.750 -0.4823 0.03498 0.02782 -0.0409 0.8345 0.0218
-6.500 -0.4667 0.03264 0.02502 -0.0392 0.8282 0.0226
-6.250 -0.4482 0.03021 0.02213 -0.0378 0.8211 0.0231
-6.000 -0.4277 0.02811 0.01959 -0.0363 0.8154 0.0239
-5.750 -0.4047 0.02630 0.01741 -0.0354 0.8093 0.0249
-5.500 -0.3810 0.02471 0.01553 -0.0344 0.8038 0.0261
-5.250 -0.3592 0.02347 0.01420 -0.0336 0.7990 0.0287
-5.000 -0.3351 0.02257 0.01316 -0.0329 0.7931 0.0329
-4.750 -0.3128 0.02138 0.01183 -0.0318 0.7882 0.0365
-4.500 -0.2900 0.02059 0.01096 -0.0309 0.7836 0.0428
-4.250 -0.2671 0.01978 0.01011 -0.0300 0.7783 0.0531
-4.000 -0.2444 0.01906 0.00931 -0.0290 0.7739 0.0706
-3.750 -0.2220 0.01827 0.00865 -0.0281 0.7697 0.1007
-3.500 -0.1992 0.01756 0.00819 -0.0274 0.7645 0.1578
-3.250 -0.1771 0.01685 0.00785 -0.0267 0.7603 0.2463
-3.000 -0.1557 0.01614 0.00757 -0.0256 0.7569 0.3598
-2.750 -0.1335 0.01550 0.00740 -0.0247 0.7518 0.4838
-2.500 -0.1083 0.01485 0.00731 -0.0238 0.7476 0.6333
-2.250 -0.0415 0.01452 0.00741 -0.0300 0.7450 0.8185
-2.000 0.0164 0.01473 0.00742 -0.0349 0.7423 0.8840
-1.750 0.0568 0.01502 0.00755 -0.0371 0.7375 0.9186
-1.500 0.0960 0.01526 0.00759 -0.0391 0.7335 0.9457
-1.250 0.1395 0.01539 0.00753 -0.0422 0.7300 0.9658
-1.000 0.1846 0.01544 0.00740 -0.0458 0.7266 0.9821
-0.750 0.2341 0.01538 0.00722 -0.0507 0.7220 0.9953
-0.500 0.2675 0.01534 0.00706 -0.0522 0.7178 1.0000
-0.250 0.2902 0.01536 0.00696 -0.0515 0.7142 1.0000
0.000 0.3139 0.01546 0.00701 -0.0512 0.7092 1.0000
0.250 0.3374 0.01555 0.00704 -0.0507 0.7044 1.0000
0.500 0.3607 0.01561 0.00702 -0.0499 0.7005 1.0000
0.750 0.3844 0.01573 0.00711 -0.0494 0.6958 1.0000
1.000 0.4080 0.01587 0.00723 -0.0490 0.6904 1.0000
1.250 0.4315 0.01595 0.00725 -0.0482 0.6862 1.0000
1.500 0.4551 0.01610 0.00739 -0.0476 0.6808 1.0000
1.750 0.4787 0.01624 0.00754 -0.0470 0.6750 1.0000
2.000 0.5023 0.01629 0.00755 -0.0461 0.6706 1.0000
2.250 0.5258 0.01650 0.00780 -0.0456 0.6638 1.0000
2.500 0.5494 0.01659 0.00789 -0.0448 0.6584 1.0000
2.750 0.5729 0.01671 0.00805 -0.0441 0.6526 1.0000
3.000 0.5962 0.01685 0.00823 -0.0434 0.6455 1.0000
3.250 0.6201 0.01687 0.00825 -0.0424 0.6400 1.0000
3.500 0.6430 0.01706 0.00854 -0.0417 0.6316 1.0000
3.750 0.6670 0.01706 0.00855 -0.0408 0.6255 1.0000
4.000 0.6898 0.01722 0.00881 -0.0400 0.6165 1.0000
4.250 0.7131 0.01727 0.00892 -0.0390 0.6085 1.0000
4.500 0.7366 0.01728 0.00902 -0.0381 0.5998 1.0000
4.750 0.7592 0.01739 0.00924 -0.0371 0.5892 1.0000
5.000 0.7822 0.01742 0.00935 -0.0361 0.5789 1.0000
5.250 0.8054 0.01739 0.00940 -0.0350 0.5679 1.0000
5.500 0.8281 0.01739 0.00952 -0.0339 0.5549 1.0000
5.750 0.8500 0.01746 0.00971 -0.0327 0.5394 1.0000
6.000 0.8714 0.01755 0.00991 -0.0315 0.5212 1.0000
6.250 0.8930 0.01759 0.01001 -0.0302 0.5011 1.0000
6.500 0.9135 0.01772 0.01020 -0.0288 0.4768 1.0000
6.750 0.9331 0.01790 0.01040 -0.0272 0.4475 1.0000
7.000 0.9509 0.01821 0.01062 -0.0254 0.4130 1.0000
7.250 0.9662 0.01874 0.01101 -0.0233 0.3743 1.0000
7.500 0.9790 0.01946 0.01157 -0.0210 0.3359 1.0000
7.750 0.9896 0.02032 0.01227 -0.0186 0.2994 1.0000
8.000 0.9990 0.02123 0.01308 -0.0161 0.2659 1.0000
8.250 1.0068 0.02221 0.01395 -0.0134 0.2355 1.0000
8.500 1.0130 0.02324 0.01491 -0.0106 0.2079 1.0000
8.750 1.0170 0.02433 0.01591 -0.0076 0.1819 1.0000
9.000 1.0181 0.02550 0.01696 -0.0043 0.1590 1.0000
9.250 1.0174 0.02668 0.01806 -0.0008 0.1380 1.0000
9.500 1.0169 0.02805 0.01932 0.0021 0.1193 1.0000
9.750 1.0194 0.02944 0.02066 0.0043 0.1025 1.0000
10.000 1.0223 0.03092 0.02212 0.0064 0.0883 1.0000
10.250 1.0252 0.03252 0.02371 0.0082 0.0769 1.0000
10.500 1.0270 0.03429 0.02545 0.0100 0.0678 1.0000
10.750 1.0303 0.03604 0.02728 0.0115 0.0591 1.0000
11.000 1.0326 0.03793 0.02921 0.0129 0.0520 1.0000
11.250 1.0338 0.03997 0.03128 0.0142 0.0470 1.0000
11.500 1.0355 0.04205 0.03345 0.0155 0.0437 1.0000
11.750 1.0386 0.04408 0.03561 0.0167 0.0404 1.0000
12.000 1.0410 0.04622 0.03783 0.0177 0.0377 1.0000
12.250 1.0403 0.04870 0.04028 0.0186 0.0353 1.0000
12.500 1.0458 0.05071 0.04252 0.0194 0.0328 1.0000
12.750 1.0495 0.05295 0.04490 0.0202 0.0308 1.0000
13.000 1.0523 0.05533 0.04741 0.0209 0.0292 1.0000
13.250 1.0536 0.05788 0.05003 0.0213 0.0278 1.0000
13.500 1.0547 0.06061 0.05281 0.0219 0.0264 1.0000
13.750 1.0560 0.06341 0.05589 0.0222 0.0253 1.0000
14.000 1.0542 0.06662 0.05934 0.0221 0.0239 1.0000
14.250 1.0517 0.07002 0.06295 0.0219 0.0229 1.0000
14.500 1.0476 0.07375 0.06687 0.0214 0.0221 1.0000
14.750 1.0423 0.07770 0.07099 0.0206 0.0215 1.0000
15.000 1.0360 0.08190 0.07534 0.0194 0.0210 1.0000
15.250 1.0286 0.08636 0.07993 0.0179 0.0204 1.0000
15.500 1.0202 0.09112 0.08480 0.0162 0.0198 1.0000
15.750 1.0102 0.09642 0.09024 0.0141 0.0195 1.0000
16.000 0.9956 0.10288 0.09689 0.0111 0.0192 1.0000
16.250 0.9808 0.10973 0.10393 0.0077 0.0192 1.0000
16.500 0.9620 0.11786 0.11227 0.0031 0.0191 1.0000
16.750 0.9450 0.12604 0.12061 -0.0015 0.0192 1.0000
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Polar data table (+)
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