EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 500,000 Max Cl/Cd: 100.67 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e562-il-500000-n5.txt Download as CSV file: xf-e562-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.6471 0.14313 0.14020 -0.0315 1.0000 0.0082
-17.500 -0.6638 0.13534 0.13233 -0.0351 1.0000 0.0083
-17.250 -0.6813 0.12773 0.12460 -0.0386 1.0000 0.0082
-17.000 -0.6923 0.12158 0.11840 -0.0414 1.0000 0.0084
-16.750 -0.7046 0.11535 0.11209 -0.0443 1.0000 0.0085
-16.500 -0.7163 0.10948 0.10614 -0.0469 1.0000 0.0085
-16.250 -0.7274 0.10384 0.10042 -0.0494 1.0000 0.0085
-16.000 -0.7378 0.09847 0.09498 -0.0519 1.0000 0.0085
-15.750 -0.7467 0.09340 0.08983 -0.0541 1.0000 0.0086
-15.500 -0.7565 0.08831 0.08467 -0.0564 1.0000 0.0088
-15.250 -0.7648 0.08360 0.07990 -0.0585 1.0000 0.0088
-15.000 -0.7743 0.07891 0.07513 -0.0605 1.0000 0.0088
-14.750 -0.7832 0.07436 0.07051 -0.0625 1.0000 0.0090
-14.500 -0.7922 0.07000 0.06608 -0.0642 1.0000 0.0090
-14.250 -0.8017 0.06575 0.06175 -0.0659 1.0000 0.0092
-14.000 -0.8117 0.06168 0.05761 -0.0673 1.0000 0.0093
-13.750 -0.8219 0.05783 0.05369 -0.0685 1.0000 0.0094
-13.500 -0.8340 0.05396 0.04975 -0.0696 1.0000 0.0094
-13.250 -0.8445 0.05044 0.04616 -0.0703 1.0000 0.0096
-13.000 -0.8586 0.04684 0.04249 -0.0707 1.0000 0.0096
-12.750 -0.8736 0.04341 0.03900 -0.0707 1.0000 0.0096
-12.500 -0.8798 0.03993 0.03543 -0.0725 0.9990 0.0098
-12.250 -0.8687 0.03623 0.03161 -0.0779 0.9955 0.0099
-12.000 -0.8594 0.03269 0.02793 -0.0829 0.9909 0.0101
-11.750 -0.8395 0.02877 0.02385 -0.0905 0.9862 0.0104
-11.500 -0.8090 0.02577 0.02071 -0.0979 0.9836 0.0107
-11.250 -0.7897 0.02415 0.01901 -0.0995 0.9782 0.0110
-11.000 -0.7617 0.02290 0.01766 -0.1019 0.9751 0.0115
-10.750 -0.7308 0.02175 0.01643 -0.1045 0.9730 0.0120
-10.500 -0.7091 0.02077 0.01536 -0.1048 0.9676 0.0126
-10.250 -0.6808 0.01989 0.01438 -0.1061 0.9638 0.0131
-10.000 -0.6499 0.01884 0.01328 -0.1082 0.9613 0.0139
-9.750 -0.6272 0.01812 0.01252 -0.1081 0.9551 0.0147
-9.500 -0.5978 0.01741 0.01173 -0.1092 0.9509 0.0156
-9.250 -0.5654 0.01674 0.01098 -0.1108 0.9481 0.0165
-9.000 -0.5425 0.01598 0.01018 -0.1105 0.9404 0.0174
-8.750 -0.5118 0.01534 0.00949 -0.1117 0.9362 0.0185
-8.500 -0.4827 0.01478 0.00886 -0.1123 0.9307 0.0196
-8.250 -0.4527 0.01418 0.00821 -0.1132 0.9244 0.0210
-8.000 -0.4176 0.01359 0.00758 -0.1150 0.9204 0.0231
-7.750 -0.3852 0.01308 0.00702 -0.1162 0.9133 0.0252
-7.500 -0.3471 0.01252 0.00642 -0.1187 0.9075 0.0288
-7.250 -0.3066 0.01196 0.00586 -0.1216 0.9008 0.0354
-7.000 -0.2626 0.01136 0.00529 -0.1254 0.8926 0.0492
-6.750 -0.2159 0.01080 0.00477 -0.1299 0.8830 0.0699
-6.500 -0.1724 0.01033 0.00433 -0.1335 0.8698 0.0923
-6.250 -0.1347 0.00999 0.00397 -0.1358 0.8534 0.1126
-6.000 -0.1018 0.00968 0.00365 -0.1371 0.8355 0.1352
-5.750 -0.0718 0.00947 0.00342 -0.1377 0.8174 0.1565
-5.500 -0.0434 0.00929 0.00321 -0.1379 0.7997 0.1797
-5.250 -0.0158 0.00915 0.00305 -0.1378 0.7827 0.2008
-5.000 0.0113 0.00906 0.00292 -0.1377 0.7661 0.2181
-4.750 0.0382 0.00899 0.00280 -0.1375 0.7503 0.2337
-4.500 0.0651 0.00895 0.00270 -0.1372 0.7351 0.2469
-4.250 0.0920 0.00891 0.00261 -0.1370 0.7204 0.2605
-4.000 0.1188 0.00889 0.00253 -0.1367 0.7061 0.2702
-3.750 0.1456 0.00890 0.00245 -0.1364 0.6922 0.2784
-3.500 0.1725 0.00889 0.00239 -0.1361 0.6787 0.2874
-3.250 0.1996 0.00890 0.00232 -0.1358 0.6655 0.2948
-3.000 0.2266 0.00890 0.00228 -0.1356 0.6527 0.3036
-2.750 0.2537 0.00891 0.00225 -0.1354 0.6405 0.3142
-2.500 0.2806 0.00894 0.00222 -0.1351 0.6285 0.3244
-2.250 0.3077 0.00896 0.00220 -0.1349 0.6163 0.3322
-2.000 0.3350 0.00899 0.00217 -0.1346 0.6048 0.3393
-1.750 0.3621 0.00902 0.00217 -0.1344 0.5939 0.3468
-1.500 0.3891 0.00908 0.00216 -0.1341 0.5826 0.3549
-1.250 0.4164 0.00911 0.00217 -0.1340 0.5718 0.3619
-1.000 0.4435 0.00916 0.00218 -0.1337 0.5619 0.3692
-0.750 0.4706 0.00922 0.00220 -0.1335 0.5514 0.3767
-0.500 0.4979 0.00927 0.00223 -0.1333 0.5415 0.3848
-0.250 0.5247 0.00935 0.00226 -0.1330 0.5320 0.3918
0.000 0.5521 0.00940 0.00231 -0.1328 0.5225 0.3998
0.250 0.5791 0.00948 0.00235 -0.1326 0.5135 0.4074
0.500 0.6061 0.00955 0.00241 -0.1324 0.5040 0.4149
0.750 0.6331 0.00963 0.00246 -0.1321 0.4957 0.4229
1.000 0.6599 0.00971 0.00254 -0.1319 0.4867 0.4304
1.250 0.6870 0.00980 0.00261 -0.1316 0.4785 0.4382
1.500 0.7136 0.00989 0.00269 -0.1313 0.4701 0.4458
1.750 0.7406 0.00998 0.00278 -0.1311 0.4622 0.4539
2.000 0.7670 0.01008 0.00287 -0.1308 0.4539 0.4613
2.250 0.7938 0.01017 0.00297 -0.1305 0.4463 0.4699
2.500 0.8202 0.01028 0.00308 -0.1302 0.4383 0.4779
2.750 0.8468 0.01039 0.00319 -0.1299 0.4311 0.4866
3.000 0.8730 0.01050 0.00332 -0.1296 0.4234 0.4954
3.250 0.8993 0.01062 0.00345 -0.1292 0.4165 0.5050
3.500 0.9256 0.01073 0.00358 -0.1289 0.4091 0.5145
3.750 0.9514 0.01086 0.00374 -0.1285 0.4024 0.5250
4.000 0.9776 0.01097 0.00388 -0.1281 0.3953 0.5363
4.500 1.0290 0.01124 0.00422 -0.1273 0.3815 0.5611
4.750 1.0542 0.01139 0.00440 -0.1268 0.3746 0.5752
5.000 1.0797 0.01152 0.00459 -0.1263 0.3680 0.5913
5.250 1.1047 0.01167 0.00479 -0.1258 0.3605 0.6087
5.500 1.1294 0.01182 0.00500 -0.1252 0.3538 0.6285
5.750 1.1542 0.01197 0.00522 -0.1246 0.3460 0.6515
6.000 1.1781 0.01214 0.00546 -0.1239 0.3387 0.6770
6.250 1.2020 0.01229 0.00570 -0.1232 0.3302 0.7073
6.500 1.2249 0.01245 0.00596 -0.1222 0.3224 0.7449
6.750 1.2468 0.01259 0.00622 -0.1210 0.3139 0.7917
7.000 1.2638 0.01266 0.00647 -0.1188 0.3064 0.8625
7.250 1.2805 0.01272 0.00664 -0.1164 0.2977 1.0000
7.500 1.3023 0.01301 0.00691 -0.1154 0.2886 1.0000
7.750 1.3225 0.01335 0.00722 -0.1140 0.2786 1.0000
8.000 1.3435 0.01367 0.00753 -0.1129 0.2680 1.0000
8.250 1.3634 0.01402 0.00787 -0.1115 0.2577 1.0000
8.500 1.3824 0.01443 0.00824 -0.1100 0.2465 1.0000
8.750 1.4009 0.01486 0.00864 -0.1085 0.2351 1.0000
9.000 1.4192 0.01529 0.00905 -0.1069 0.2236 1.0000
9.250 1.4362 0.01578 0.00952 -0.1052 0.2114 1.0000
9.500 1.4519 0.01634 0.01003 -0.1033 0.1979 1.0000
9.750 1.4658 0.01699 0.01062 -0.1012 0.1827 1.0000
10.000 1.4781 0.01773 0.01129 -0.0989 0.1661 1.0000
10.250 1.4887 0.01856 0.01204 -0.0965 0.1497 1.0000
10.500 1.4988 0.01942 0.01284 -0.0940 0.1352 1.0000
10.750 1.5090 0.02029 0.01368 -0.0916 0.1229 1.0000
11.000 1.5185 0.02121 0.01458 -0.0893 0.1120 1.0000
11.250 1.5268 0.02223 0.01557 -0.0869 0.1017 1.0000
11.500 1.5340 0.02335 0.01668 -0.0845 0.0925 1.0000
11.750 1.5405 0.02455 0.01788 -0.0822 0.0837 1.0000
12.000 1.5474 0.02579 0.01912 -0.0801 0.0762 1.0000
12.250 1.5516 0.02726 0.02059 -0.0779 0.0688 1.0000
12.500 1.5545 0.02890 0.02223 -0.0758 0.0612 1.0000
12.750 1.5586 0.03055 0.02390 -0.0740 0.0552 1.0000
13.000 1.5603 0.03248 0.02584 -0.0723 0.0494 1.0000
13.250 1.5626 0.03446 0.02786 -0.0708 0.0447 1.0000
13.500 1.5637 0.03664 0.03008 -0.0695 0.0403 1.0000
13.750 1.5647 0.03895 0.03244 -0.0684 0.0368 1.0000
14.000 1.5652 0.04142 0.03497 -0.0675 0.0339 1.0000
14.250 1.5654 0.04404 0.03764 -0.0668 0.0309 1.0000
14.500 1.5639 0.04695 0.04062 -0.0663 0.0287 1.0000
14.750 1.5636 0.04983 0.04357 -0.0660 0.0267 1.0000
15.000 1.5615 0.05304 0.04686 -0.0659 0.0248 1.0000
15.250 1.5584 0.05649 0.05038 -0.0660 0.0232 1.0000
15.500 1.5564 0.05991 0.05390 -0.0662 0.0217 1.0000
15.750 1.5521 0.06372 0.05780 -0.0667 0.0203 1.0000
16.000 1.5465 0.06785 0.06201 -0.0673 0.0191 1.0000
16.250 1.5431 0.07177 0.06603 -0.0681 0.0182 1.0000
16.500 1.5381 0.07600 0.07035 -0.0690 0.0171 1.0000
16.750 1.5322 0.08048 0.07493 -0.0702 0.0162 1.0000
17.000 1.5254 0.08519 0.07973 -0.0715 0.0154 1.0000
17.250 1.5205 0.08970 0.08434 -0.0729 0.0146 1.0000
17.500 1.5145 0.09444 0.08918 -0.0745 0.0139 1.0000
17.750 1.5079 0.09936 0.09420 -0.0762 0.0132 1.0000
18.000 1.5007 0.10446 0.09939 -0.0781 0.0126 1.0000
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Polar data table (+)
Polar graphs
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