E221 (9.39%) (e221-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E221 (9.39%) (e221-il) Reynolds number: 50,000 Max Cl/Cd: 29.42 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e221-il-50000.txt Download as CSV file: xf-e221-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: E221 (9.39%)
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5169 0.12196 0.11528 0.0125 1.0000 0.2098
-9.500 -0.5083 0.11761 0.11097 0.0121 1.0000 0.2161
-9.250 -0.5177 0.11584 0.10929 0.0100 1.0000 0.2255
-9.000 -0.4977 0.11056 0.10398 0.0110 1.0000 0.2342
-8.750 -0.5060 0.10805 0.10159 0.0091 1.0000 0.2424
-8.500 -0.5045 0.10516 0.09874 0.0085 1.0000 0.2544
-8.250 -0.4877 0.10048 0.09408 0.0093 1.0000 0.2654
-8.000 -0.4831 0.09694 0.09060 0.0091 1.0000 0.2761
-7.750 -0.4823 0.09374 0.08748 0.0087 1.0000 0.2886
-7.500 -0.4774 0.09038 0.08419 0.0090 1.0000 0.3038
-7.250 -0.4706 0.08711 0.08097 0.0097 1.0000 0.3221
-7.000 -0.4790 0.08487 0.07885 0.0099 1.0000 0.3418
-6.000 -0.4995 0.05532 0.04852 -0.0235 1.0000 0.1375
-5.750 -0.4878 0.04982 0.04261 -0.0239 1.0000 0.1218
-5.500 -0.4774 0.04506 0.03699 -0.0232 1.0000 0.1111
-5.250 -0.4618 0.04153 0.03319 -0.0220 1.0000 0.1103
-5.000 -0.4459 0.03835 0.02965 -0.0205 1.0000 0.1098
-4.750 -0.4293 0.03542 0.02630 -0.0188 1.0000 0.1097
-4.500 -0.4114 0.03270 0.02316 -0.0169 1.0000 0.1100
-4.250 -0.3928 0.03040 0.02040 -0.0149 1.0000 0.1118
-4.000 -0.3751 0.02841 0.01845 -0.0133 1.0000 0.1208
-3.750 -0.3564 0.02658 0.01640 -0.0115 1.0000 0.1306
-3.500 -0.3374 0.02496 0.01473 -0.0097 1.0000 0.1476
-3.250 -0.3175 0.02337 0.01318 -0.0081 1.0000 0.1812
-3.000 -0.0918 0.01730 0.00976 -0.0332 1.0000 1.0000
-2.750 -0.0870 0.01698 0.00922 -0.0313 1.0000 1.0000
-2.500 -0.0867 0.01693 0.00901 -0.0282 1.0000 1.0000
-2.250 -0.0914 0.01710 0.00900 -0.0242 1.0000 1.0000
-2.000 -0.0957 0.01737 0.00908 -0.0202 1.0000 1.0000
-1.750 -0.0963 0.01768 0.00915 -0.0168 1.0000 1.0000
-1.500 -0.0936 0.01802 0.00927 -0.0140 1.0000 1.0000
-1.250 -0.0886 0.01838 0.00943 -0.0116 1.0000 1.0000
-1.000 -0.0816 0.01878 0.00963 -0.0095 1.0000 1.0000
-0.750 -0.0730 0.01921 0.00987 -0.0077 1.0000 1.0000
-0.500 -0.0397 0.01984 0.01028 -0.0106 0.9922 1.0000
-0.250 0.0193 0.02064 0.01082 -0.0180 0.9749 1.0000
0.000 0.0784 0.02136 0.01136 -0.0253 0.9582 1.0000
0.250 0.1307 0.02197 0.01182 -0.0310 0.9406 1.0000
0.500 0.1812 0.02252 0.01228 -0.0361 0.9230 1.0000
0.750 0.2349 0.02300 0.01271 -0.0416 0.9058 1.0000
1.000 0.2871 0.02340 0.01308 -0.0465 0.8889 1.0000
1.250 0.3341 0.02376 0.01344 -0.0502 0.8723 1.0000
1.500 0.3750 0.02414 0.01383 -0.0524 0.8554 1.0000
1.750 0.4012 0.02472 0.01442 -0.0523 0.8371 1.0000
2.000 0.4294 0.02526 0.01497 -0.0522 0.8194 1.0000
2.250 0.4575 0.02576 0.01552 -0.0519 0.8023 1.0000
2.500 0.4846 0.02624 0.01603 -0.0513 0.7856 1.0000
2.750 0.5106 0.02671 0.01654 -0.0503 0.7693 1.0000
3.000 0.5303 0.02740 0.01727 -0.0487 0.7517 1.0000
3.250 0.5497 0.02809 0.01805 -0.0470 0.7337 1.0000
3.500 0.5711 0.02867 0.01869 -0.0453 0.7164 1.0000
3.750 0.5934 0.02916 0.01924 -0.0435 0.6993 1.0000
4.000 0.6165 0.02952 0.01968 -0.0416 0.6824 1.0000
4.250 0.6372 0.03005 0.02032 -0.0396 0.6647 1.0000
4.500 0.6551 0.03079 0.02116 -0.0376 0.6453 1.0000
4.750 0.6771 0.03111 0.02158 -0.0354 0.6268 1.0000
5.000 0.7016 0.03114 0.02169 -0.0330 0.6090 1.0000
5.250 0.7195 0.03183 0.02254 -0.0310 0.5879 1.0000
5.500 0.7427 0.03187 0.02269 -0.0285 0.5678 1.0000
5.750 0.7648 0.03200 0.02292 -0.0261 0.5467 1.0000
6.000 0.7878 0.03196 0.02298 -0.0235 0.5242 1.0000
6.250 0.8090 0.03212 0.02329 -0.0211 0.5001 1.0000
6.500 0.8341 0.03172 0.02293 -0.0183 0.4756 1.0000
6.750 0.8591 0.03132 0.02253 -0.0156 0.4489 1.0000
7.000 0.8807 0.03136 0.02262 -0.0132 0.4193 1.0000
7.250 0.9003 0.03162 0.02297 -0.0107 0.3872 1.0000
7.500 0.9209 0.03178 0.02310 -0.0082 0.3535 1.0000
7.750 0.9418 0.03201 0.02317 -0.0058 0.3186 1.0000
8.000 0.9578 0.03290 0.02404 -0.0034 0.2827 1.0000
8.250 0.9745 0.03392 0.02485 -0.0010 0.2468 1.0000
8.500 0.9874 0.03529 0.02610 0.0014 0.2109 1.0000
8.750 0.9985 0.03687 0.02748 0.0036 0.1773 1.0000
9.000 1.0092 0.03905 0.02955 0.0057 0.1500 1.0000
9.250 1.0193 0.04173 0.03239 0.0077 0.1310 1.0000
9.500 1.0315 0.04508 0.03596 0.0094 0.1198 1.0000
9.750 1.0462 0.04832 0.03921 0.0106 0.1108 1.0000
10.000 1.0447 0.05198 0.04347 0.0126 0.1064 1.0000
10.250 1.0600 0.05512 0.04655 0.0136 0.0995 1.0000
10.500 1.0569 0.05950 0.05129 0.0151 0.0983 1.0000
10.750 1.0452 0.06382 0.05601 0.0167 0.0980 1.0000
11.000 1.0302 0.06817 0.06065 0.0179 0.0980 1.0000
11.250 1.0115 0.07246 0.06513 0.0191 0.0983 1.0000
11.500 0.9922 0.07714 0.06994 0.0191 0.0987 1.0000
11.750 0.9011 0.08913 0.08221 0.0095 0.1098 1.0000
12.000 0.8805 0.09719 0.09025 0.0053 0.1112 1.0000
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Polar data table (+)
Polar graphs
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