E226 (10.19%) (e226-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E226 (10.19%) (e226-il) Reynolds number: 500,000 Max Cl/Cd: 67.25 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e226-il-500000-n5.txt Download as CSV file: xf-e226-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E226 (10.19%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7644 0.07335 0.07082 -0.0235 1.0000 0.0073
-12.000 -0.8324 0.05407 0.05108 -0.0390 1.0000 0.0068
-11.750 -0.8435 0.04894 0.04581 -0.0431 1.0000 0.0069
-11.500 -0.8627 0.04380 0.04047 -0.0459 1.0000 0.0069
-11.250 -0.8700 0.04106 0.03759 -0.0462 1.0000 0.0070
-11.000 -0.8824 0.03829 0.03464 -0.0447 1.0000 0.0070
-10.750 -0.8912 0.03595 0.03210 -0.0419 1.0000 0.0070
-10.500 -0.8893 0.03386 0.02981 -0.0402 1.0000 0.0071
-10.250 -0.8848 0.03166 0.02738 -0.0385 1.0000 0.0071
-10.000 -0.8770 0.02959 0.02507 -0.0369 1.0000 0.0072
-9.750 -0.8664 0.02766 0.02291 -0.0353 1.0000 0.0072
-9.500 -0.8531 0.02601 0.02105 -0.0338 1.0000 0.0073
-9.250 -0.8383 0.02447 0.01932 -0.0324 1.0000 0.0073
-9.000 -0.8221 0.02313 0.01780 -0.0310 1.0000 0.0075
-8.750 -0.8052 0.02190 0.01641 -0.0296 1.0000 0.0077
-8.500 -0.7880 0.02077 0.01514 -0.0282 1.0000 0.0078
-8.250 -0.7706 0.01973 0.01397 -0.0266 1.0000 0.0079
-8.000 -0.7530 0.01881 0.01294 -0.0251 1.0000 0.0081
-7.750 -0.7354 0.01797 0.01198 -0.0234 1.0000 0.0083
-7.500 -0.7136 0.01714 0.01106 -0.0227 0.9988 0.0084
-7.250 -0.6824 0.01630 0.01012 -0.0238 0.9947 0.0087
-7.000 -0.6522 0.01553 0.00927 -0.0247 0.9901 0.0089
-6.750 -0.6203 0.01485 0.00851 -0.0259 0.9863 0.0090
-6.500 -0.5907 0.01395 0.00753 -0.0268 0.9811 0.0093
-6.250 -0.5607 0.01318 0.00671 -0.0276 0.9751 0.0100
-6.000 -0.5299 0.01264 0.00612 -0.0285 0.9693 0.0105
-5.750 -0.4997 0.01216 0.00558 -0.0292 0.9621 0.0110
-5.500 -0.4692 0.01172 0.00507 -0.0299 0.9549 0.0114
-5.250 -0.4397 0.01134 0.00462 -0.0303 0.9462 0.0119
-5.000 -0.4113 0.01102 0.00423 -0.0304 0.9367 0.0125
-4.750 -0.3835 0.01068 0.00382 -0.0303 0.9269 0.0137
-4.500 -0.3569 0.01040 0.00349 -0.0300 0.9156 0.0155
-4.250 -0.3313 0.01001 0.00315 -0.0295 0.9039 0.0287
-4.000 -0.3069 0.00948 0.00282 -0.0290 0.8919 0.0727
-3.750 -0.2818 0.00910 0.00256 -0.0285 0.8801 0.1117
-3.500 -0.2563 0.00880 0.00235 -0.0280 0.8679 0.1464
-3.250 -0.2309 0.00850 0.00216 -0.0276 0.8553 0.1869
-3.000 -0.2050 0.00824 0.00199 -0.0272 0.8425 0.2243
-2.750 -0.1802 0.00785 0.00184 -0.0268 0.8296 0.2949
-2.500 -0.1549 0.00754 0.00171 -0.0263 0.8164 0.3561
-2.250 -0.1287 0.00738 0.00161 -0.0260 0.8029 0.3894
-2.000 -0.1022 0.00725 0.00151 -0.0256 0.7891 0.4202
-1.750 -0.0758 0.00712 0.00143 -0.0253 0.7749 0.4532
-1.500 -0.0494 0.00702 0.00136 -0.0249 0.7602 0.4849
-1.250 -0.0229 0.00692 0.00130 -0.0246 0.7451 0.5167
-1.000 0.0036 0.00684 0.00126 -0.0242 0.7295 0.5478
-0.750 0.0301 0.00676 0.00122 -0.0239 0.7137 0.5784
-0.500 0.0565 0.00670 0.00120 -0.0235 0.6975 0.6091
-0.250 0.0829 0.00665 0.00119 -0.0231 0.6810 0.6397
0.000 0.1092 0.00661 0.00119 -0.0227 0.6640 0.6696
0.250 0.1354 0.00659 0.00120 -0.0223 0.6467 0.6988
0.500 0.1615 0.00658 0.00122 -0.0218 0.6290 0.7271
0.750 0.1876 0.00658 0.00125 -0.0213 0.6103 0.7546
1.000 0.2136 0.00659 0.00129 -0.0208 0.5909 0.7815
1.250 0.2395 0.00663 0.00134 -0.0202 0.5709 0.8076
1.500 0.2652 0.00668 0.00140 -0.0196 0.5505 0.8324
1.750 0.2910 0.00674 0.00147 -0.0190 0.5292 0.8560
2.000 0.3167 0.00683 0.00155 -0.0184 0.5081 0.8791
2.250 0.3430 0.00693 0.00163 -0.0179 0.4852 0.9008
2.500 0.3708 0.00707 0.00173 -0.0178 0.4619 0.9218
2.750 0.4009 0.00724 0.00185 -0.0182 0.4360 0.9405
3.000 0.4334 0.00744 0.00197 -0.0192 0.4091 0.9552
3.250 0.4668 0.00766 0.00209 -0.0205 0.3810 0.9668
3.500 0.5000 0.00789 0.00224 -0.0218 0.3533 0.9764
3.750 0.5326 0.00814 0.00240 -0.0229 0.3258 0.9850
4.000 0.5669 0.00845 0.00257 -0.0246 0.2901 0.9909
4.250 0.5992 0.00891 0.00280 -0.0259 0.2379 0.9972
4.500 0.6264 0.00937 0.00305 -0.0262 0.1923 1.0000
4.750 0.6478 0.00979 0.00330 -0.0251 0.1576 1.0000
5.000 0.6698 0.01017 0.00357 -0.0241 0.1301 1.0000
5.250 0.6917 0.01057 0.00385 -0.0232 0.1048 1.0000
5.500 0.7142 0.01095 0.00414 -0.0223 0.0849 1.0000
5.750 0.7362 0.01141 0.00449 -0.0213 0.0622 1.0000
6.000 0.7578 0.01194 0.00489 -0.0203 0.0395 1.0000
6.250 0.7785 0.01261 0.00541 -0.0193 0.0160 1.0000
6.500 0.8012 0.01307 0.00585 -0.0184 0.0120 1.0000
6.750 0.8246 0.01347 0.00629 -0.0177 0.0109 1.0000
7.000 0.8476 0.01391 0.00677 -0.0169 0.0100 1.0000
7.250 0.8699 0.01445 0.00739 -0.0160 0.0092 1.0000
7.500 0.8926 0.01494 0.00794 -0.0152 0.0089 1.0000
7.750 0.9150 0.01546 0.00853 -0.0144 0.0086 1.0000
8.000 0.9368 0.01603 0.00917 -0.0135 0.0083 1.0000
8.250 0.9582 0.01663 0.00985 -0.0126 0.0079 1.0000
8.500 0.9793 0.01725 0.01053 -0.0117 0.0075 1.0000
8.750 0.9994 0.01795 0.01129 -0.0106 0.0072 1.0000
9.000 1.0183 0.01873 0.01214 -0.0095 0.0069 1.0000
9.250 1.0359 0.01962 0.01311 -0.0082 0.0067 1.0000
9.500 1.0509 0.02072 0.01429 -0.0066 0.0065 1.0000
9.750 1.0638 0.02197 0.01565 -0.0047 0.0064 1.0000
10.000 1.0799 0.02286 0.01663 -0.0033 0.0063 1.0000
10.250 1.0948 0.02380 0.01767 -0.0017 0.0062 1.0000
10.500 1.1071 0.02491 0.01889 0.0001 0.0062 1.0000
10.750 1.1172 0.02595 0.02004 0.0023 0.0060 1.0000
11.000 1.1244 0.02712 0.02133 0.0048 0.0060 1.0000
11.250 1.1312 0.02834 0.02267 0.0071 0.0059 1.0000
11.500 1.1359 0.02980 0.02427 0.0092 0.0058 1.0000
11.750 1.1398 0.03138 0.02599 0.0112 0.0057 1.0000
12.000 1.1427 0.03312 0.02788 0.0128 0.0056 1.0000
12.250 1.1442 0.03509 0.02998 0.0142 0.0056 1.0000
12.500 1.1440 0.03733 0.03238 0.0152 0.0054 1.0000
12.750 1.1419 0.03993 0.03515 0.0159 0.0054 1.0000
13.000 1.1386 0.04284 0.03821 0.0160 0.0054 1.0000
13.250 1.1343 0.04604 0.04158 0.0157 0.0054 1.0000
13.500 1.1284 0.04968 0.04538 0.0149 0.0054 1.0000
13.750 1.1199 0.05394 0.04981 0.0134 0.0053 1.0000
14.000 1.1097 0.05873 0.05477 0.0113 0.0053 1.0000
14.250 1.0996 0.06382 0.06002 0.0087 0.0053 1.0000
14.500 1.0861 0.06980 0.06617 0.0054 0.0053 1.0000
14.750 1.0705 0.07650 0.07304 0.0016 0.0053 1.0000
15.000 1.0544 0.08370 0.08039 -0.0027 0.0054 1.0000
15.250 1.0371 0.09157 0.08843 -0.0074 0.0054 1.0000
15.500 1.0191 0.10008 0.09707 -0.0126 0.0053 1.0000
15.750 0.9970 0.10982 0.10696 -0.0184 0.0053 1.0000
16.000 0.9738 0.12038 0.11768 -0.0245 0.0054 1.0000
16.250 0.9480 0.13209 0.12953 -0.0312 0.0055 1.0000
16.500 0.9140 0.14708 0.14466 -0.0393 0.0057 1.0000
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Polar data table (+)
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