E226 (10.19%) (e226-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E226 (10.19%) (e226-il) Reynolds number: 1,000,000 Max Cl/Cd: 73.41 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e226-il-1000000-n5.txt Download as CSV file: xf-e226-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8343 0.08845 0.08649 -0.0142 1.0000 0.0048
-13.750 -0.8810 0.07398 0.07183 -0.0230 1.0000 0.0047
-13.500 -0.9242 0.06070 0.05833 -0.0322 1.0000 0.0046
-13.250 -0.9376 0.05382 0.05132 -0.0374 1.0000 0.0046
-13.000 -0.9564 0.04674 0.04406 -0.0429 1.0000 0.0046
-12.750 -0.9763 0.04082 0.03793 -0.0467 1.0000 0.0046
-12.500 -0.9797 0.03795 0.03496 -0.0478 1.0000 0.0047
-12.250 -0.9912 0.03483 0.03167 -0.0475 1.0000 0.0047
-12.000 -1.0033 0.03224 0.02890 -0.0454 1.0000 0.0047
-11.750 -1.0048 0.03079 0.02734 -0.0427 1.0000 0.0047
-11.500 -1.0032 0.02904 0.02543 -0.0405 1.0000 0.0048
-11.250 -0.9939 0.02765 0.02391 -0.0389 1.0000 0.0048
-11.000 -0.9829 0.02626 0.02237 -0.0374 1.0000 0.0049
-10.750 -0.9700 0.02495 0.02093 -0.0360 1.0000 0.0049
-10.500 -0.9542 0.02389 0.01974 -0.0348 1.0000 0.0050
-10.250 -0.9388 0.02267 0.01838 -0.0335 1.0000 0.0051
-10.000 -0.9223 0.02155 0.01713 -0.0323 1.0000 0.0052
-9.750 -0.9053 0.02045 0.01590 -0.0310 1.0000 0.0053
-9.500 -0.8877 0.01942 0.01475 -0.0297 1.0000 0.0054
-9.250 -0.8701 0.01845 0.01367 -0.0283 1.0000 0.0054
-9.000 -0.8518 0.01763 0.01276 -0.0269 1.0000 0.0055
-8.750 -0.8334 0.01687 0.01191 -0.0255 1.0000 0.0057
-8.500 -0.8075 0.01609 0.01103 -0.0256 0.9977 0.0058
-8.250 -0.7783 0.01527 0.01012 -0.0264 0.9936 0.0059
-8.000 -0.7486 0.01461 0.00939 -0.0272 0.9894 0.0060
-7.750 -0.7171 0.01407 0.00878 -0.0284 0.9857 0.0062
-7.500 -0.6875 0.01351 0.00815 -0.0291 0.9802 0.0062
-7.250 -0.6584 0.01268 0.00723 -0.0298 0.9737 0.0065
-7.000 -0.6303 0.01201 0.00649 -0.0301 0.9654 0.0067
-6.750 -0.6017 0.01150 0.00593 -0.0305 0.9568 0.0069
-6.500 -0.5750 0.01108 0.00545 -0.0304 0.9458 0.0071
-6.250 -0.5491 0.01073 0.00504 -0.0300 0.9343 0.0073
-6.000 -0.5237 0.01040 0.00465 -0.0296 0.9228 0.0075
-5.750 -0.4983 0.01011 0.00429 -0.0290 0.9111 0.0078
-5.500 -0.4727 0.00986 0.00397 -0.0286 0.8990 0.0082
-5.250 -0.4468 0.00963 0.00368 -0.0281 0.8866 0.0086
-5.000 -0.4207 0.00941 0.00340 -0.0277 0.8745 0.0089
-4.750 -0.3946 0.00918 0.00310 -0.0273 0.8622 0.0093
-4.500 -0.3683 0.00896 0.00280 -0.0270 0.8500 0.0100
-4.250 -0.3418 0.00879 0.00256 -0.0266 0.8370 0.0107
-4.000 -0.3151 0.00863 0.00235 -0.0264 0.8239 0.0118
-3.750 -0.2883 0.00848 0.00215 -0.0261 0.8108 0.0148
-3.500 -0.2625 0.00812 0.00190 -0.0257 0.7977 0.0452
-3.250 -0.2369 0.00777 0.00168 -0.0254 0.7840 0.0866
-3.000 -0.2109 0.00747 0.00150 -0.0251 0.7702 0.1283
-2.750 -0.1843 0.00728 0.00137 -0.0249 0.7559 0.1590
-2.500 -0.1576 0.00711 0.00126 -0.0247 0.7414 0.1891
-2.250 -0.1313 0.00689 0.00115 -0.0245 0.7262 0.2334
-2.000 -0.1057 0.00656 0.00104 -0.0242 0.7110 0.3054
-1.750 -0.0791 0.00640 0.00097 -0.0240 0.6955 0.3476
-1.500 -0.0519 0.00632 0.00091 -0.0238 0.6796 0.3736
-1.250 -0.0249 0.00624 0.00086 -0.0237 0.6636 0.4034
-1.000 0.0022 0.00618 0.00083 -0.0235 0.6468 0.4319
-0.750 0.0294 0.00612 0.00080 -0.0234 0.6300 0.4602
-0.500 0.0565 0.00608 0.00078 -0.0232 0.6130 0.4880
-0.250 0.0836 0.00604 0.00077 -0.0231 0.5957 0.5159
0.000 0.1108 0.00601 0.00077 -0.0229 0.5776 0.5442
0.250 0.1378 0.00599 0.00077 -0.0227 0.5587 0.5732
0.500 0.1647 0.00599 0.00079 -0.0225 0.5391 0.6011
0.750 0.1917 0.00600 0.00081 -0.0224 0.5193 0.6287
1.000 0.2186 0.00601 0.00085 -0.0222 0.4988 0.6567
1.250 0.2454 0.00604 0.00089 -0.0219 0.4782 0.6841
1.500 0.2721 0.00607 0.00094 -0.0217 0.4575 0.7112
1.750 0.2986 0.00612 0.00101 -0.0214 0.4363 0.7383
2.000 0.3251 0.00619 0.00108 -0.0211 0.4139 0.7637
2.500 0.3775 0.00636 0.00125 -0.0204 0.3666 0.8126
2.750 0.4035 0.00647 0.00136 -0.0200 0.3441 0.8362
3.000 0.4292 0.00658 0.00147 -0.0195 0.3208 0.8595
3.250 0.4548 0.00670 0.00159 -0.0190 0.3003 0.8833
3.500 0.4801 0.00683 0.00172 -0.0184 0.2785 0.9071
3.750 0.5045 0.00717 0.00190 -0.0177 0.2310 0.9305
4.000 0.5313 0.00760 0.00213 -0.0177 0.1765 0.9514
4.250 0.5628 0.00791 0.00233 -0.0186 0.1484 0.9667
4.500 0.5951 0.00822 0.00253 -0.0198 0.1231 0.9774
4.750 0.6266 0.00856 0.00276 -0.0208 0.0982 0.9857
5.000 0.6592 0.00898 0.00303 -0.0221 0.0690 0.9913
5.250 0.6905 0.00944 0.00335 -0.0232 0.0428 0.9968
5.500 0.7196 0.00989 0.00368 -0.0237 0.0228 1.0000
5.750 0.7412 0.01034 0.00405 -0.0226 0.0102 1.0000
6.000 0.7648 0.01061 0.00434 -0.0218 0.0087 1.0000
6.250 0.7885 0.01089 0.00463 -0.0211 0.0080 1.0000
6.500 0.8123 0.01118 0.00495 -0.0204 0.0075 1.0000
6.750 0.8361 0.01151 0.00530 -0.0196 0.0071 1.0000
7.000 0.8596 0.01189 0.00572 -0.0189 0.0067 1.0000
7.250 0.8830 0.01229 0.00616 -0.0182 0.0063 1.0000
7.500 0.9069 0.01263 0.00652 -0.0176 0.0060 1.0000
7.750 0.9304 0.01302 0.00696 -0.0169 0.0058 1.0000
8.000 0.9537 0.01345 0.00742 -0.0162 0.0056 1.0000
8.250 0.9767 0.01389 0.00792 -0.0155 0.0054 1.0000
8.500 0.9994 0.01436 0.00843 -0.0147 0.0053 1.0000
8.750 1.0217 0.01488 0.00899 -0.0139 0.0051 1.0000
9.000 1.0434 0.01542 0.00959 -0.0131 0.0049 1.0000
9.250 1.0648 0.01599 0.01021 -0.0122 0.0048 1.0000
9.500 1.0856 0.01660 0.01088 -0.0113 0.0047 1.0000
9.750 1.1054 0.01727 0.01162 -0.0102 0.0046 1.0000
10.000 1.1230 0.01813 0.01255 -0.0089 0.0044 1.0000
10.250 1.1384 0.01914 0.01365 -0.0073 0.0043 1.0000
10.500 1.1528 0.02019 0.01480 -0.0056 0.0043 1.0000
10.750 1.1702 0.02089 0.01558 -0.0043 0.0042 1.0000
11.000 1.1848 0.02178 0.01656 -0.0027 0.0041 1.0000
11.250 1.1997 0.02256 0.01743 -0.0011 0.0041 1.0000
11.500 1.2102 0.02344 0.01839 0.0011 0.0040 1.0000
11.750 1.2165 0.02445 0.01950 0.0039 0.0040 1.0000
12.000 1.2232 0.02549 0.02063 0.0063 0.0039 1.0000
12.250 1.2291 0.02663 0.02187 0.0085 0.0039 1.0000
12.500 1.2345 0.02789 0.02323 0.0105 0.0038 1.0000
12.750 1.2352 0.02960 0.02506 0.0125 0.0038 1.0000
13.000 1.2352 0.03150 0.02708 0.0141 0.0038 1.0000
13.250 1.2363 0.03347 0.02917 0.0152 0.0037 1.0000
13.500 1.2356 0.03576 0.03159 0.0159 0.0037 1.0000
13.750 1.2335 0.03840 0.03435 0.0162 0.0036 1.0000
14.000 1.2271 0.04174 0.03783 0.0160 0.0036 1.0000
14.250 1.2253 0.04478 0.04099 0.0153 0.0036 1.0000
14.500 1.2173 0.04885 0.04520 0.0141 0.0036 1.0000
14.750 1.2078 0.05344 0.04994 0.0122 0.0035 1.0000
15.000 1.1976 0.05840 0.05503 0.0099 0.0036 1.0000
15.250 1.1929 0.06282 0.05955 0.0075 0.0035 1.0000
15.500 1.1711 0.07026 0.06717 0.0036 0.0035 1.0000
15.750 1.1534 0.07742 0.07447 -0.0004 0.0035 1.0000
16.000 1.1385 0.08440 0.08158 -0.0044 0.0035 1.0000
16.250 1.1173 0.09283 0.09015 -0.0092 0.0035 1.0000
16.500 1.1002 0.10080 0.09823 -0.0138 0.0035 1.0000
16.750 1.0838 0.10893 0.10647 -0.0184 0.0035 1.0000
17.000 1.0551 0.11993 0.11763 -0.0246 0.0036 1.0000
17.250 1.0329 0.13003 0.12785 -0.0304 0.0036 1.0000
17.500 1.0116 0.14025 0.13818 -0.0361 0.0036 1.0000
17.750 0.9956 0.14953 0.14756 -0.0413 0.0036 1.0000
18.000 0.9676 0.16252 0.16066 -0.0485 0.0037 1.0000
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Polar data table (+)
Polar graphs
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