E226 (10.19%) (e226-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E226 (10.19%) (e226-il) Reynolds number: 200,000 Max Cl/Cd: 55.34 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e226-il-200000-n5.txt Download as CSV file: xf-e226-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6641 0.08685 0.08322 -0.0170 1.0000 0.0133
-11.250 -0.7300 0.06452 0.06047 -0.0351 1.0000 0.0125
-11.000 -0.7461 0.05837 0.05418 -0.0401 1.0000 0.0125
-10.750 -0.7654 0.05309 0.04873 -0.0435 1.0000 0.0125
-10.500 -0.7807 0.04931 0.04478 -0.0443 1.0000 0.0124
-10.250 -0.7959 0.04622 0.04148 -0.0428 1.0000 0.0124
-10.000 -0.8039 0.04326 0.03826 -0.0411 1.0000 0.0124
-9.750 -0.8061 0.04029 0.03498 -0.0395 1.0000 0.0124
-9.500 -0.8043 0.03745 0.03179 -0.0379 1.0000 0.0124
-9.250 -0.7970 0.03497 0.02900 -0.0363 1.0000 0.0125
-9.000 -0.7873 0.03265 0.02635 -0.0348 1.0000 0.0125
-8.750 -0.7762 0.03011 0.02353 -0.0332 1.0000 0.0127
-8.500 -0.7619 0.02809 0.02131 -0.0318 1.0000 0.0129
-8.250 -0.7458 0.02643 0.01945 -0.0305 1.0000 0.0131
-8.000 -0.7288 0.02498 0.01784 -0.0291 1.0000 0.0133
-7.750 -0.7115 0.02378 0.01654 -0.0277 1.0000 0.0139
-7.500 -0.6936 0.02272 0.01536 -0.0263 1.0000 0.0144
-7.250 -0.6756 0.02172 0.01425 -0.0248 1.0000 0.0152
-7.000 -0.6578 0.02069 0.01311 -0.0232 1.0000 0.0156
-6.750 -0.6404 0.01972 0.01204 -0.0216 1.0000 0.0159
-6.500 -0.6233 0.01883 0.01106 -0.0198 1.0000 0.0162
-6.250 -0.6063 0.01804 0.01017 -0.0180 1.0000 0.0166
-6.000 -0.5894 0.01729 0.00935 -0.0162 1.0000 0.0169
-5.750 -0.5649 0.01646 0.00845 -0.0161 0.9975 0.0178
-5.500 -0.5315 0.01577 0.00766 -0.0176 0.9923 0.0189
-5.250 -0.4974 0.01518 0.00696 -0.0192 0.9870 0.0207
-5.000 -0.4640 0.01455 0.00631 -0.0207 0.9815 0.0255
-4.750 -0.4308 0.01388 0.00568 -0.0220 0.9756 0.0390
-4.500 -0.3977 0.01312 0.00513 -0.0236 0.9702 0.0834
-4.250 -0.3670 0.01246 0.00474 -0.0246 0.9627 0.1397
-4.000 -0.3341 0.01188 0.00441 -0.0261 0.9567 0.1999
-3.750 -0.3047 0.01136 0.00415 -0.0268 0.9479 0.2664
-3.500 -0.2738 0.01088 0.00394 -0.0277 0.9403 0.3331
-3.250 -0.2439 0.01052 0.00375 -0.0282 0.9313 0.3866
-3.000 -0.2146 0.01025 0.00356 -0.0284 0.9216 0.4274
-2.750 -0.1844 0.01000 0.00340 -0.0288 0.9127 0.4669
-2.500 -0.1570 0.00978 0.00327 -0.0286 0.9015 0.5056
-2.250 -0.1299 0.00957 0.00316 -0.0283 0.8901 0.5427
-2.000 -0.1029 0.00940 0.00305 -0.0278 0.8788 0.5790
-1.750 -0.0762 0.00923 0.00296 -0.0273 0.8673 0.6139
-1.500 -0.0503 0.00909 0.00289 -0.0266 0.8547 0.6481
-1.250 -0.0246 0.00897 0.00283 -0.0258 0.8416 0.6814
-1.000 0.0011 0.00888 0.00279 -0.0249 0.8282 0.7138
-0.750 0.0267 0.00880 0.00276 -0.0241 0.8145 0.7446
-0.500 0.0524 0.00874 0.00273 -0.0232 0.8003 0.7737
-0.250 0.0783 0.00870 0.00272 -0.0223 0.7858 0.8020
0.000 0.1045 0.00868 0.00271 -0.0215 0.7707 0.8287
0.250 0.1314 0.00869 0.00271 -0.0209 0.7551 0.8541
0.500 0.1598 0.00871 0.00272 -0.0206 0.7389 0.8773
0.750 0.1894 0.00876 0.00273 -0.0205 0.7221 0.8987
1.000 0.2216 0.00882 0.00275 -0.0211 0.7046 0.9169
1.250 0.2553 0.00890 0.00277 -0.0221 0.6860 0.9332
1.500 0.2899 0.00898 0.00279 -0.0233 0.6658 0.9478
1.750 0.3246 0.00908 0.00283 -0.0246 0.6447 0.9608
2.000 0.3594 0.00919 0.00287 -0.0260 0.6220 0.9730
2.250 0.3957 0.00932 0.00291 -0.0277 0.5979 0.9828
2.500 0.4329 0.00944 0.00297 -0.0298 0.5719 0.9914
2.750 0.4697 0.00959 0.00303 -0.0318 0.5448 1.0000
3.000 0.4914 0.00976 0.00312 -0.0306 0.5202 1.0000
3.500 0.5353 0.01018 0.00338 -0.0284 0.4679 1.0000
3.750 0.5574 0.01042 0.00353 -0.0273 0.4404 1.0000
4.000 0.5795 0.01069 0.00372 -0.0263 0.4126 1.0000
4.250 0.6015 0.01098 0.00394 -0.0252 0.3845 1.0000
4.500 0.6235 0.01130 0.00417 -0.0242 0.3549 1.0000
4.750 0.6453 0.01166 0.00443 -0.0231 0.3233 1.0000
5.250 0.6886 0.01251 0.00506 -0.0211 0.2542 1.0000
5.500 0.7096 0.01305 0.00542 -0.0201 0.2150 1.0000
5.750 0.7306 0.01363 0.00583 -0.0191 0.1750 1.0000
6.000 0.7515 0.01425 0.00629 -0.0181 0.1386 1.0000
6.250 0.7722 0.01492 0.00679 -0.0172 0.1053 1.0000
6.500 0.7930 0.01561 0.00733 -0.0163 0.0771 1.0000
6.750 0.8138 0.01630 0.00792 -0.0153 0.0548 1.0000
7.000 0.8338 0.01710 0.00863 -0.0142 0.0351 1.0000
7.250 0.8537 0.01795 0.00947 -0.0131 0.0235 1.0000
7.500 0.8738 0.01874 0.01029 -0.0120 0.0194 1.0000
7.750 0.8936 0.01954 0.01114 -0.0109 0.0168 1.0000
8.000 0.9131 0.02037 0.01207 -0.0097 0.0155 1.0000
8.250 0.9320 0.02122 0.01305 -0.0085 0.0147 1.0000
8.500 0.9501 0.02213 0.01408 -0.0073 0.0140 1.0000
8.750 0.9668 0.02313 0.01519 -0.0059 0.0134 1.0000
9.000 0.9820 0.02425 0.01641 -0.0043 0.0130 1.0000
9.250 0.9952 0.02552 0.01776 -0.0026 0.0126 1.0000
9.500 1.0069 0.02695 0.01928 -0.0008 0.0124 1.0000
9.750 1.0199 0.02826 0.02072 0.0009 0.0122 1.0000
10.000 1.0319 0.02965 0.02226 0.0027 0.0119 1.0000
10.250 1.0424 0.03100 0.02378 0.0046 0.0116 1.0000
10.500 1.0508 0.03253 0.02546 0.0067 0.0115 1.0000
10.750 1.0578 0.03404 0.02715 0.0087 0.0109 1.0000
11.000 1.0637 0.03575 0.02902 0.0105 0.0107 1.0000
11.250 1.0681 0.03750 0.03093 0.0122 0.0104 1.0000
11.500 1.0702 0.03959 0.03320 0.0137 0.0102 1.0000
11.750 1.0708 0.04192 0.03573 0.0149 0.0101 1.0000
12.000 1.0695 0.04448 0.03848 0.0158 0.0100 1.0000
12.250 1.0663 0.04737 0.04156 0.0163 0.0099 1.0000
12.500 1.0608 0.05061 0.04499 0.0162 0.0098 1.0000
12.750 1.0530 0.05440 0.04899 0.0155 0.0098 1.0000
13.000 1.0431 0.05874 0.05358 0.0142 0.0098 1.0000
13.250 1.0322 0.06347 0.05851 0.0121 0.0098 1.0000
13.500 1.0184 0.06908 0.06433 0.0092 0.0098 1.0000
13.750 1.0030 0.07532 0.07076 0.0056 0.0097 1.0000
14.000 0.9835 0.08294 0.07860 0.0009 0.0098 1.0000
14.250 0.9614 0.09171 0.08757 -0.0048 0.0100 1.0000
14.500 0.9351 0.10227 0.09834 -0.0117 0.0101 1.0000
14.750 0.8933 0.11813 0.11443 -0.0215 0.0104 1.0000
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Polar data table (+)
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