EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 562 AIRFOIL (e562-il) Reynolds number: 500,000 Max Cl/Cd: 104.91 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e562-il-500000.txt Download as CSV file: xf-e562-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7025 0.08821 0.08500 -0.0594 1.0000 0.0139
-14.750 -0.7282 0.08021 0.07682 -0.0638 1.0000 0.0137
-14.500 -0.7325 0.07625 0.07283 -0.0658 1.0000 0.0140
-14.250 -0.7450 0.07113 0.06761 -0.0685 1.0000 0.0142
-14.000 -0.7604 0.06598 0.06232 -0.0709 1.0000 0.0141
-13.750 -0.7718 0.06172 0.05797 -0.0727 1.0000 0.0141
-13.500 -0.7805 0.05799 0.05416 -0.0742 1.0000 0.0143
-13.250 -0.7909 0.05425 0.05032 -0.0754 1.0000 0.0143
-13.000 -0.7971 0.05118 0.04720 -0.0763 1.0000 0.0146
-12.750 -0.8078 0.04783 0.04373 -0.0768 1.0000 0.0145
-12.500 -0.8152 0.04505 0.04089 -0.0770 1.0000 0.0147
-12.250 -0.8256 0.04226 0.03801 -0.0767 1.0000 0.0148
-12.000 -0.8366 0.03978 0.03547 -0.0761 1.0000 0.0151
-11.750 -0.8531 0.03750 0.03312 -0.0741 1.0000 0.0150
-11.500 -0.8774 0.03537 0.03092 -0.0713 1.0000 0.0151
-11.250 -0.8657 0.03268 0.02807 -0.0752 0.9982 0.0154
-11.000 -0.8347 0.03040 0.02560 -0.0804 0.9948 0.0158
-10.750 -0.8042 0.02868 0.02370 -0.0841 0.9912 0.0162
-10.500 -0.7774 0.02634 0.02124 -0.0872 0.9873 0.0167
-10.250 -0.7445 0.02473 0.01959 -0.0907 0.9848 0.0174
-10.000 -0.7134 0.02351 0.01832 -0.0932 0.9814 0.0181
-9.750 -0.6827 0.02234 0.01706 -0.0953 0.9772 0.0189
-9.500 -0.6476 0.02137 0.01598 -0.0979 0.9748 0.0198
-9.250 -0.6125 0.01978 0.01433 -0.1013 0.9729 0.0210
-9.000 -0.5851 0.01887 0.01339 -0.1022 0.9674 0.0222
-8.750 -0.5506 0.01806 0.01251 -0.1043 0.9642 0.0237
-8.500 -0.5145 0.01691 0.01128 -0.1071 0.9620 0.0253
-8.250 -0.4765 0.01603 0.01036 -0.1099 0.9604 0.0274
-8.000 -0.4509 0.01539 0.00965 -0.1098 0.9531 0.0291
-7.750 -0.4147 0.01446 0.00870 -0.1122 0.9503 0.0326
-7.500 -0.3769 0.01372 0.00792 -0.1146 0.9484 0.0372
-7.250 -0.3486 0.01302 0.00722 -0.1150 0.9417 0.0440
-7.000 -0.3137 0.01207 0.00640 -0.1170 0.9380 0.0670
-6.750 -0.2770 0.01120 0.00571 -0.1193 0.9354 0.1043
-6.500 -0.2466 0.01060 0.00521 -0.1200 0.9291 0.1328
-6.250 -0.2124 0.01006 0.00477 -0.1215 0.9238 0.1637
-6.000 -0.1727 0.00959 0.00438 -0.1240 0.9204 0.1908
-5.750 -0.1390 0.00929 0.00410 -0.1252 0.9116 0.2120
-5.500 -0.0952 0.00898 0.00380 -0.1285 0.9063 0.2317
-5.250 -0.0538 0.00876 0.00359 -0.1313 0.8973 0.2501
-4.750 0.0323 0.00846 0.00322 -0.1375 0.8750 0.2835
-4.500 0.0689 0.00839 0.00307 -0.1393 0.8595 0.2955
-4.250 0.1024 0.00839 0.00296 -0.1403 0.8429 0.3073
-4.000 0.1330 0.00835 0.00286 -0.1407 0.8259 0.3169
-3.750 0.1621 0.00836 0.00276 -0.1408 0.8090 0.3260
-3.500 0.1899 0.00837 0.00270 -0.1407 0.7921 0.3349
-3.250 0.2173 0.00839 0.00263 -0.1404 0.7759 0.3430
-2.750 0.2711 0.00845 0.00256 -0.1397 0.7444 0.3617
-2.500 0.2979 0.00852 0.00253 -0.1394 0.7294 0.3713
-2.250 0.3246 0.00853 0.00251 -0.1390 0.7147 0.3791
-2.000 0.3514 0.00859 0.00249 -0.1386 0.7005 0.3872
-1.750 0.3780 0.00861 0.00248 -0.1383 0.6868 0.3952
-1.500 0.4048 0.00869 0.00247 -0.1379 0.6735 0.4036
-1.250 0.4314 0.00873 0.00248 -0.1375 0.6605 0.4110
-1.000 0.4581 0.00880 0.00249 -0.1372 0.6476 0.4193
-0.750 0.4848 0.00884 0.00250 -0.1368 0.6352 0.4272
-0.500 0.5116 0.00892 0.00253 -0.1365 0.6231 0.4357
-0.250 0.5381 0.00899 0.00256 -0.1361 0.6115 0.4433
0.000 0.5649 0.00906 0.00260 -0.1358 0.5999 0.4519
0.250 0.5917 0.00912 0.00264 -0.1355 0.5886 0.4599
0.500 0.6182 0.00922 0.00269 -0.1352 0.5778 0.4685
0.750 0.6448 0.00929 0.00275 -0.1348 0.5670 0.4769
1.000 0.6716 0.00937 0.00281 -0.1345 0.5566 0.4858
1.250 0.6980 0.00947 0.00288 -0.1341 0.5465 0.4942
1.500 0.7247 0.00955 0.00296 -0.1338 0.5364 0.5038
1.750 0.7512 0.00963 0.00304 -0.1335 0.5269 0.5127
2.000 0.7775 0.00975 0.00313 -0.1331 0.5173 0.5227
2.250 0.8042 0.00982 0.00324 -0.1328 0.5080 0.5328
2.500 0.8301 0.00995 0.00334 -0.1324 0.4992 0.5433
2.750 0.8568 0.01003 0.00345 -0.1321 0.4902 0.5550
3.000 0.8828 0.01015 0.00358 -0.1317 0.4820 0.5671
3.250 0.9092 0.01023 0.00371 -0.1314 0.4732 0.5802
3.500 0.9350 0.01036 0.00385 -0.1310 0.4654 0.5946
3.750 0.9612 0.01045 0.00400 -0.1306 0.4571 0.6112
4.000 0.9867 0.01059 0.00416 -0.1301 0.4495 0.6297
4.250 1.0128 0.01067 0.00433 -0.1297 0.4416 0.6515
4.500 1.0378 0.01082 0.00452 -0.1292 0.4341 0.6764
4.750 1.0634 0.01088 0.00470 -0.1287 0.4263 0.7066
5.000 1.0873 0.01103 0.00491 -0.1279 0.4190 0.7434
5.250 1.1114 0.01104 0.00511 -0.1270 0.4116 0.7906
5.500 1.1305 0.01109 0.00531 -0.1251 0.4045 0.8574
5.750 1.1492 0.01101 0.00539 -0.1229 0.3975 1.0000
6.000 1.1739 0.01124 0.00558 -0.1224 0.3896 1.0000
6.250 1.1990 0.01144 0.00579 -0.1219 0.3819 1.0000
6.500 1.2230 0.01168 0.00600 -0.1212 0.3739 1.0000
6.750 1.2474 0.01189 0.00622 -0.1206 0.3661 1.0000
7.000 1.2707 0.01214 0.00646 -0.1198 0.3579 1.0000
7.250 1.2943 0.01237 0.00670 -0.1190 0.3499 1.0000
7.500 1.3157 0.01265 0.00694 -0.1178 0.3413 1.0000
7.750 1.3381 0.01287 0.00720 -0.1168 0.3326 1.0000
8.000 1.3579 0.01320 0.00749 -0.1154 0.3240 1.0000
8.250 1.3799 0.01343 0.00776 -0.1143 0.3149 1.0000
8.500 1.3995 0.01376 0.00807 -0.1129 0.3059 1.0000
8.750 1.4194 0.01409 0.00840 -0.1115 0.2964 1.0000
9.000 1.4393 0.01442 0.00875 -0.1102 0.2867 1.0000
9.250 1.4569 0.01483 0.00914 -0.1085 0.2763 1.0000
9.500 1.4747 0.01525 0.00954 -0.1068 0.2646 1.0000
9.750 1.4919 0.01569 0.00998 -0.1051 0.2516 1.0000
10.000 1.5079 0.01620 0.01046 -0.1033 0.2382 1.0000
10.250 1.5226 0.01678 0.01100 -0.1012 0.2247 1.0000
10.500 1.5363 0.01741 0.01160 -0.0991 0.2110 1.0000
10.750 1.5486 0.01812 0.01227 -0.0969 0.1972 1.0000
11.000 1.5596 0.01891 0.01302 -0.0945 0.1828 1.0000
11.250 1.5689 0.01980 0.01387 -0.0920 0.1679 1.0000
11.500 1.5763 0.02082 0.01483 -0.0894 0.1526 1.0000
11.750 1.5825 0.02195 0.01591 -0.0867 0.1384 1.0000
12.000 1.5872 0.02321 0.01713 -0.0841 0.1248 1.0000
12.250 1.5910 0.02459 0.01847 -0.0815 0.1126 1.0000
12.500 1.5937 0.02610 0.01996 -0.0790 0.1015 1.0000
12.750 1.5954 0.02777 0.02162 -0.0767 0.0920 1.0000
13.000 1.5967 0.02957 0.02341 -0.0745 0.0829 1.0000
13.250 1.5986 0.03143 0.02529 -0.0727 0.0751 1.0000
13.500 1.5982 0.03358 0.02745 -0.0709 0.0683 1.0000
13.750 1.5976 0.03587 0.02977 -0.0695 0.0620 1.0000
14.000 1.5971 0.03828 0.03222 -0.0682 0.0566 1.0000
14.250 1.5936 0.04112 0.03508 -0.0672 0.0514 1.0000
14.500 1.5923 0.04387 0.03790 -0.0664 0.0471 1.0000
14.750 1.5875 0.04713 0.04120 -0.0659 0.0432 1.0000
15.000 1.5839 0.05040 0.04454 -0.0655 0.0397 1.0000
15.250 1.5784 0.05402 0.04823 -0.0655 0.0365 1.0000
15.500 1.5709 0.05806 0.05233 -0.0657 0.0339 1.0000
15.750 1.5665 0.06182 0.05620 -0.0660 0.0315 1.0000
16.000 1.5580 0.06628 0.06071 -0.0667 0.0295 1.0000
16.250 1.5490 0.07095 0.06548 -0.0676 0.0277 1.0000
16.500 1.5431 0.07531 0.06995 -0.0685 0.0261 1.0000
16.750 1.5343 0.08021 0.07493 -0.0698 0.0246 1.0000
17.000 1.5215 0.08586 0.08066 -0.0714 0.0234 1.0000
17.250 1.5146 0.09071 0.08562 -0.0729 0.0223 1.0000
17.500 1.5081 0.09556 0.09058 -0.0745 0.0212 1.0000
17.750 1.4992 0.10089 0.09599 -0.0765 0.0202 1.0000
18.000 1.4877 0.10676 0.10195 -0.0787 0.0194 1.0000
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Polar data table (+)
Polar graphs
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