EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.42 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e562-il-1000000.txt Download as CSV file: xf-e562-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 562 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.7070 0.13516 0.13289 -0.0342 1.0000 0.0087
-17.750 -0.7290 0.12668 0.12429 -0.0383 1.0000 0.0087
-17.500 -0.7468 0.11933 0.11684 -0.0418 1.0000 0.0087
-17.250 -0.7595 0.11320 0.11063 -0.0447 1.0000 0.0088
-17.000 -0.7731 0.10710 0.10444 -0.0476 1.0000 0.0087
-16.750 -0.7811 0.10203 0.09931 -0.0500 1.0000 0.0088
-16.500 -0.7918 0.09669 0.09389 -0.0524 1.0000 0.0088
-16.250 -0.8011 0.09159 0.08873 -0.0548 1.0000 0.0090
-16.000 -0.8118 0.08654 0.08360 -0.0571 1.0000 0.0089
-15.750 -0.8223 0.08167 0.07865 -0.0593 1.0000 0.0089
-15.500 -0.8288 0.07728 0.07420 -0.0613 1.0000 0.0092
-15.250 -0.8384 0.07283 0.06967 -0.0631 1.0000 0.0091
-15.000 -0.8479 0.06843 0.06521 -0.0649 1.0000 0.0092
-14.750 -0.8583 0.06414 0.06085 -0.0666 1.0000 0.0092
-14.500 -0.8661 0.06024 0.05688 -0.0681 1.0000 0.0094
-14.250 -0.8765 0.05637 0.05294 -0.0694 1.0000 0.0095
-14.000 -0.8878 0.05262 0.04912 -0.0704 1.0000 0.0095
-13.750 -0.9024 0.04875 0.04518 -0.0712 1.0000 0.0095
-13.500 -0.9149 0.04527 0.04164 -0.0717 1.0000 0.0095
-13.250 -0.9314 0.04175 0.03805 -0.0717 1.0000 0.0095
-13.000 -0.9454 0.03876 0.03499 -0.0712 1.0000 0.0097
-12.750 -0.9653 0.03508 0.03123 -0.0714 0.9993 0.0096
-12.500 -0.9488 0.03168 0.02772 -0.0776 0.9955 0.0098
-12.250 -0.9226 0.02813 0.02404 -0.0855 0.9925 0.0100
-12.000 -0.8924 0.02584 0.02163 -0.0913 0.9891 0.0102
-11.750 -0.8630 0.02343 0.01906 -0.0966 0.9863 0.0104
-11.500 -0.8317 0.02131 0.01685 -0.1012 0.9846 0.0110
-11.250 -0.7969 0.02052 0.01602 -0.1041 0.9838 0.0115
-11.000 -0.7750 0.01954 0.01498 -0.1043 0.9788 0.0118
-10.750 -0.7435 0.01869 0.01407 -0.1062 0.9766 0.0123
-10.500 -0.7098 0.01791 0.01322 -0.1084 0.9751 0.0127
-10.250 -0.6752 0.01730 0.01255 -0.1105 0.9739 0.0131
-10.000 -0.6411 0.01598 0.01116 -0.1134 0.9729 0.0141
-9.750 -0.6181 0.01534 0.01048 -0.1130 0.9676 0.0147
-9.500 -0.5862 0.01476 0.00986 -0.1143 0.9649 0.0154
-9.250 -0.5519 0.01426 0.00931 -0.1160 0.9632 0.0162
-9.000 -0.5172 0.01339 0.00839 -0.1182 0.9617 0.0174
-8.750 -0.4813 0.01285 0.00783 -0.1202 0.9606 0.0186
-8.500 -0.4598 0.01242 0.00736 -0.1191 0.9532 0.0196
-8.250 -0.4266 0.01179 0.00670 -0.1205 0.9505 0.0213
-8.000 -0.3921 0.01127 0.00616 -0.1221 0.9483 0.0231
-7.750 -0.3677 0.01089 0.00573 -0.1215 0.9407 0.0245
-7.500 -0.3349 0.01032 0.00516 -0.1227 0.9365 0.0279
-7.250 -0.2995 0.00981 0.00466 -0.1244 0.9322 0.0335
-7.000 -0.2651 0.00923 0.00415 -0.1261 0.9250 0.0496
-6.750 -0.2214 0.00856 0.00362 -0.1298 0.9203 0.0797
-6.500 -0.1780 0.00808 0.00324 -0.1334 0.9118 0.1066
-6.250 -0.1285 0.00767 0.00290 -0.1383 0.9029 0.1360
-6.000 -0.0877 0.00735 0.00264 -0.1413 0.8873 0.1660
-5.750 -0.0539 0.00718 0.00245 -0.1426 0.8680 0.1872
-5.500 -0.0240 0.00708 0.00231 -0.1430 0.8480 0.2042
-5.250 0.0038 0.00702 0.00220 -0.1429 0.8286 0.2198
-5.000 0.0307 0.00699 0.00210 -0.1426 0.8101 0.2340
-4.750 0.0572 0.00697 0.00202 -0.1423 0.7923 0.2466
-4.500 0.0838 0.00696 0.00196 -0.1419 0.7754 0.2590
-4.250 0.1103 0.00694 0.00189 -0.1415 0.7590 0.2709
-4.000 0.1368 0.00694 0.00184 -0.1411 0.7431 0.2809
-3.500 0.1904 0.00695 0.00175 -0.1405 0.7127 0.3000
-3.250 0.2175 0.00698 0.00171 -0.1402 0.6984 0.3075
-3.000 0.2446 0.00698 0.00168 -0.1399 0.6843 0.3166
-2.750 0.2717 0.00702 0.00165 -0.1397 0.6711 0.3237
-2.500 0.2988 0.00704 0.00163 -0.1394 0.6582 0.3327
-2.250 0.3259 0.00709 0.00162 -0.1391 0.6449 0.3418
-2.000 0.3533 0.00710 0.00162 -0.1390 0.6323 0.3518
-1.750 0.3808 0.00714 0.00162 -0.1388 0.6205 0.3593
-1.500 0.4081 0.00718 0.00162 -0.1386 0.6086 0.3671
-1.250 0.4352 0.00725 0.00163 -0.1383 0.5967 0.3744
-1.000 0.4630 0.00727 0.00165 -0.1382 0.5857 0.3827
-0.750 0.4904 0.00734 0.00166 -0.1380 0.5748 0.3897
-0.500 0.5175 0.00739 0.00169 -0.1378 0.5637 0.3974
-0.250 0.5452 0.00745 0.00172 -0.1377 0.5532 0.4047
0.000 0.5727 0.00750 0.00176 -0.1375 0.5433 0.4128
0.500 0.6275 0.00763 0.00184 -0.1371 0.5231 0.4278
0.750 0.6546 0.00772 0.00190 -0.1369 0.5136 0.4358
1.000 0.6820 0.00778 0.00195 -0.1367 0.5039 0.4435
1.250 0.7093 0.00786 0.00201 -0.1366 0.4949 0.4516
1.500 0.7363 0.00795 0.00208 -0.1363 0.4857 0.4593
1.750 0.7637 0.00802 0.00215 -0.1362 0.4772 0.4675
2.000 0.7904 0.00812 0.00223 -0.1359 0.4682 0.4754
2.250 0.8179 0.00818 0.00231 -0.1357 0.4603 0.4844
2.500 0.8444 0.00830 0.00240 -0.1354 0.4518 0.4928
2.750 0.8718 0.00836 0.00249 -0.1353 0.4444 0.5022
3.000 0.8982 0.00848 0.00260 -0.1349 0.4361 0.5119
3.250 0.9255 0.00856 0.00269 -0.1348 0.4291 0.5219
3.500 0.9519 0.00867 0.00281 -0.1344 0.4212 0.5331
3.750 0.9787 0.00875 0.00292 -0.1342 0.4143 0.5452
4.000 1.0051 0.00886 0.00304 -0.1339 0.4066 0.5579
4.500 1.0579 0.00907 0.00331 -0.1333 0.3922 0.5889
4.750 1.0838 0.00919 0.00346 -0.1329 0.3851 0.6070
5.000 1.1102 0.00928 0.00361 -0.1326 0.3777 0.6282
5.250 1.1356 0.00941 0.00378 -0.1321 0.3701 0.6525
5.500 1.1617 0.00950 0.00394 -0.1318 0.3626 0.6800
5.750 1.1865 0.00964 0.00414 -0.1312 0.3547 0.7133
6.000 1.2122 0.00971 0.00432 -0.1308 0.3472 0.7534
6.250 1.2357 0.00983 0.00454 -0.1299 0.3392 0.8037
6.500 1.2571 0.00981 0.00473 -0.1285 0.3321 0.8795
6.750 1.2756 0.00986 0.00487 -0.1264 0.3234 1.0000
7.000 1.3007 0.01005 0.00505 -0.1259 0.3151 1.0000
7.250 1.3245 0.01029 0.00526 -0.1252 0.3062 1.0000
7.500 1.3481 0.01052 0.00547 -0.1245 0.2969 1.0000
7.750 1.3710 0.01076 0.00569 -0.1235 0.2880 1.0000
8.000 1.3923 0.01106 0.00594 -0.1224 0.2780 1.0000
8.250 1.4144 0.01131 0.00618 -0.1213 0.2679 1.0000
8.500 1.4353 0.01161 0.00646 -0.1201 0.2577 1.0000
8.750 1.4548 0.01198 0.00677 -0.1186 0.2451 1.0000
9.000 1.4732 0.01239 0.00711 -0.1170 0.2301 1.0000
9.250 1.4912 0.01283 0.00749 -0.1153 0.2161 1.0000
9.500 1.5086 0.01329 0.00789 -0.1135 0.2023 1.0000
9.750 1.5248 0.01379 0.00833 -0.1116 0.1880 1.0000
10.000 1.5401 0.01434 0.00881 -0.1095 0.1735 1.0000
10.250 1.5543 0.01494 0.00934 -0.1074 0.1580 1.0000
10.500 1.5667 0.01562 0.00994 -0.1049 0.1422 1.0000
10.750 1.5776 0.01637 0.01062 -0.1023 0.1264 1.0000
11.000 1.5869 0.01721 0.01137 -0.0996 0.1114 1.0000
11.250 1.5969 0.01802 0.01213 -0.0970 0.0996 1.0000
11.500 1.6057 0.01890 0.01297 -0.0943 0.0887 1.0000
11.750 1.6137 0.01984 0.01387 -0.0917 0.0791 1.0000
12.250 1.6284 0.02189 0.01587 -0.0866 0.0633 1.0000
12.500 1.6353 0.02300 0.01699 -0.0842 0.0572 1.0000
12.750 1.6401 0.02430 0.01827 -0.0818 0.0512 1.0000
13.000 1.6466 0.02554 0.01954 -0.0797 0.0465 1.0000
13.250 1.6493 0.02712 0.02111 -0.0774 0.0414 1.0000
13.500 1.6542 0.02862 0.02265 -0.0755 0.0376 1.0000
13.750 1.6562 0.03043 0.02448 -0.0736 0.0339 1.0000
14.000 1.6585 0.03232 0.02640 -0.0720 0.0303 1.0000
14.250 1.6598 0.03440 0.02851 -0.0705 0.0276 1.0000
14.500 1.6609 0.03660 0.03076 -0.0693 0.0250 1.0000
14.750 1.6603 0.03908 0.03329 -0.0682 0.0228 1.0000
15.000 1.6608 0.04158 0.03585 -0.0673 0.0210 1.0000
15.250 1.6580 0.04453 0.03885 -0.0666 0.0192 1.0000
15.500 1.6576 0.04735 0.04175 -0.0662 0.0180 1.0000
15.750 1.6555 0.05048 0.04495 -0.0660 0.0168 1.0000
16.000 1.6511 0.05400 0.04853 -0.0659 0.0158 1.0000
16.250 1.6474 0.05756 0.05217 -0.0661 0.0149 1.0000
16.500 1.6444 0.06114 0.05585 -0.0664 0.0142 1.0000
16.750 1.6388 0.06518 0.05997 -0.0670 0.0134 1.0000
17.000 1.6317 0.06956 0.06443 -0.0678 0.0127 1.0000
17.250 1.6234 0.07423 0.06919 -0.0688 0.0121 1.0000
17.500 1.6193 0.07839 0.07345 -0.0699 0.0116 1.0000
17.750 1.6128 0.08301 0.07817 -0.0712 0.0111 1.0000
18.000 1.6049 0.08795 0.08320 -0.0727 0.0107 1.0000
18.250 1.5954 0.09322 0.08856 -0.0744 0.0102 1.0000
18.500 1.5830 0.09908 0.09451 -0.0765 0.0098 1.0000
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Polar data table (+)
Polar graphs
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