EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 561 AIRFOIL (e561-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.3 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e561-il-1000000-n5.txt Download as CSV file: xf-e561-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 561 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6958 0.09697 0.09393 -0.0600 1.0000 0.0094
-16.000 -0.7025 0.09271 0.08962 -0.0618 1.0000 0.0094
-15.750 -0.7098 0.08845 0.08531 -0.0635 1.0000 0.0095
-15.500 -0.7097 0.08373 0.08053 -0.0673 0.9994 0.0095
-15.250 -0.7109 0.07859 0.07532 -0.0718 0.9986 0.0095
-15.000 -0.7097 0.07380 0.07047 -0.0762 0.9975 0.0096
-14.750 -0.7091 0.06885 0.06544 -0.0810 0.9962 0.0096
-14.500 -0.7073 0.06404 0.06055 -0.0859 0.9949 0.0097
-14.250 -0.7069 0.05900 0.05543 -0.0913 0.9937 0.0097
-14.000 -0.7131 0.05425 0.05061 -0.0952 0.9919 0.0097
-13.750 -0.7177 0.04970 0.04597 -0.0992 0.9894 0.0098
-13.500 -0.7233 0.04469 0.04088 -0.1042 0.9867 0.0097
-13.250 -0.7198 0.04026 0.03635 -0.1097 0.9842 0.0098
-13.000 -0.7297 0.03571 0.03172 -0.1132 0.9787 0.0098
-12.500 -0.7492 0.02713 0.02293 -0.1190 0.9539 0.0098
-12.250 -0.7311 0.02268 0.01830 -0.1274 0.9410 0.0099
-12.000 -0.6994 0.02022 0.01570 -0.1331 0.9326 0.0101
-11.750 -0.6586 0.01863 0.01400 -0.1384 0.9235 0.0104
-11.500 -0.6023 0.01732 0.01259 -0.1462 0.9151 0.0106
-11.250 -0.5405 0.01628 0.01142 -0.1546 0.8992 0.0110
-11.000 -0.5021 0.01566 0.01061 -0.1578 0.8688 0.0112
-10.750 -0.4788 0.01521 0.00999 -0.1577 0.8392 0.0114
-10.500 -0.4576 0.01483 0.00946 -0.1571 0.8151 0.0117
-10.250 -0.4358 0.01446 0.00896 -0.1564 0.7948 0.0119
-10.000 -0.4134 0.01411 0.00848 -0.1558 0.7761 0.0121
-9.750 -0.3902 0.01377 0.00804 -0.1553 0.7599 0.0123
-9.500 -0.3664 0.01347 0.00763 -0.1549 0.7440 0.0124
-9.250 -0.3425 0.01308 0.00714 -0.1545 0.7292 0.0129
-9.000 -0.3175 0.01274 0.00672 -0.1543 0.7162 0.0132
-8.750 -0.2922 0.01244 0.00634 -0.1540 0.7038 0.0137
-8.500 -0.2668 0.01219 0.00600 -0.1537 0.6906 0.0141
-8.250 -0.2406 0.01194 0.00569 -0.1536 0.6782 0.0147
-8.000 -0.2140 0.01172 0.00539 -0.1534 0.6675 0.0152
-7.750 -0.1878 0.01149 0.00509 -0.1532 0.6565 0.0162
-7.500 -0.1607 0.01126 0.00480 -0.1532 0.6457 0.0176
-7.250 -0.1340 0.01103 0.00452 -0.1531 0.6351 0.0201
-7.000 -0.1071 0.01072 0.00420 -0.1531 0.6244 0.0281
-6.750 -0.0800 0.01036 0.00388 -0.1532 0.6158 0.0424
-6.500 -0.0527 0.01007 0.00360 -0.1532 0.6065 0.0560
-6.250 -0.0251 0.00982 0.00337 -0.1533 0.5978 0.0699
-6.000 0.0023 0.00958 0.00315 -0.1533 0.5878 0.0862
-5.750 0.0303 0.00938 0.00297 -0.1534 0.5792 0.1015
-5.500 0.0582 0.00922 0.00281 -0.1535 0.5707 0.1166
-5.250 0.0865 0.00908 0.00268 -0.1535 0.5636 0.1293
-5.000 0.1146 0.00896 0.00257 -0.1536 0.5554 0.1432
-4.750 0.1428 0.00885 0.00247 -0.1536 0.5479 0.1567
-4.500 0.1710 0.00878 0.00239 -0.1537 0.5396 0.1669
-4.250 0.1992 0.00873 0.00232 -0.1537 0.5322 0.1777
-4.000 0.2277 0.00866 0.00226 -0.1537 0.5256 0.1900
-3.750 0.2559 0.00862 0.00221 -0.1537 0.5186 0.2007
-3.500 0.2843 0.00859 0.00217 -0.1537 0.5123 0.2096
-3.250 0.3127 0.00858 0.00214 -0.1537 0.5051 0.2169
-3.000 0.3407 0.00860 0.00211 -0.1537 0.4984 0.2232
-2.750 0.3693 0.00857 0.00209 -0.1537 0.4928 0.2303
-2.500 0.3976 0.00858 0.00207 -0.1537 0.4867 0.2369
-2.250 0.4257 0.00860 0.00206 -0.1536 0.4809 0.2438
-2.000 0.4541 0.00860 0.00206 -0.1537 0.4752 0.2513
-1.750 0.4822 0.00863 0.00206 -0.1536 0.4691 0.2575
-1.500 0.5103 0.00865 0.00207 -0.1535 0.4639 0.2650
-1.250 0.5387 0.00867 0.00208 -0.1535 0.4593 0.2715
-1.000 0.5668 0.00869 0.00210 -0.1535 0.4539 0.2781
-0.750 0.5945 0.00875 0.00213 -0.1534 0.4484 0.2851
-0.500 0.6227 0.00877 0.00215 -0.1534 0.4441 0.2918
-0.250 0.6508 0.00880 0.00218 -0.1533 0.4396 0.2990
0.000 0.6786 0.00886 0.00222 -0.1532 0.4349 0.3050
0.250 0.7062 0.00892 0.00227 -0.1531 0.4304 0.3121
0.500 0.7343 0.00895 0.00232 -0.1530 0.4263 0.3198
0.750 0.7621 0.00901 0.00237 -0.1529 0.4220 0.3252
1.000 0.7896 0.00907 0.00243 -0.1528 0.4179 0.3327
1.250 0.8168 0.00915 0.00250 -0.1526 0.4137 0.3401
1.500 0.8447 0.00919 0.00256 -0.1525 0.4102 0.3464
1.750 0.8722 0.00925 0.00264 -0.1524 0.4062 0.3537
2.000 0.8994 0.00933 0.00271 -0.1522 0.4023 0.3602
2.250 0.9262 0.00942 0.00280 -0.1520 0.3981 0.3677
2.500 0.9536 0.00949 0.00289 -0.1518 0.3949 0.3746
2.750 0.9808 0.00955 0.00297 -0.1516 0.3913 0.3816
3.000 1.0078 0.00963 0.00307 -0.1514 0.3876 0.3898
3.250 1.0342 0.00974 0.00317 -0.1511 0.3835 0.3963
3.500 1.0606 0.00984 0.00328 -0.1508 0.3798 0.4045
3.750 1.0876 0.00991 0.00339 -0.1506 0.3768 0.4134
4.000 1.1142 0.00999 0.00350 -0.1503 0.3732 0.4216
4.250 1.1401 0.01010 0.00362 -0.1500 0.3691 0.4310
4.500 1.1656 0.01023 0.00376 -0.1495 0.3650 0.4411
4.750 1.1919 0.01032 0.00389 -0.1492 0.3621 0.4518
5.000 1.2180 0.01041 0.00402 -0.1489 0.3585 0.4631
5.250 1.2435 0.01052 0.00417 -0.1484 0.3545 0.4764
5.500 1.2683 0.01066 0.00433 -0.1479 0.3504 0.4911
5.750 1.2930 0.01078 0.00449 -0.1473 0.3468 0.5065
6.000 1.3178 0.01087 0.00464 -0.1467 0.3432 0.5254
6.250 1.3418 0.01098 0.00482 -0.1460 0.3390 0.5468
6.500 1.3647 0.01112 0.00500 -0.1451 0.3346 0.5696
6.750 1.3880 0.01125 0.00520 -0.1443 0.3306 0.5981
7.000 1.4118 0.01136 0.00540 -0.1436 0.3265 0.6318
7.250 1.4346 0.01150 0.00563 -0.1427 0.3217 0.6696
7.500 1.4561 0.01167 0.00590 -0.1416 0.3166 0.7172
7.750 1.4788 0.01175 0.00615 -0.1407 0.3121 0.7838
8.000 1.4934 0.01164 0.00637 -0.1380 0.3068 0.9788
8.500 1.5350 0.01216 0.00686 -0.1356 0.2949 1.0000
8.750 1.5546 0.01247 0.00716 -0.1343 0.2879 1.0000
9.000 1.5746 0.01277 0.00745 -0.1330 0.2821 1.0000
9.250 1.5942 0.01309 0.00776 -0.1317 0.2748 1.0000
9.500 1.6120 0.01348 0.00813 -0.1301 0.2674 1.0000
9.750 1.6288 0.01391 0.00852 -0.1283 0.2578 1.0000
10.000 1.6449 0.01437 0.00896 -0.1265 0.2481 1.0000
10.250 1.6584 0.01495 0.00949 -0.1244 0.2374 1.0000
10.500 1.6722 0.01552 0.01003 -0.1223 0.2269 1.0000
10.750 1.6831 0.01623 0.01068 -0.1199 0.2143 1.0000
11.000 1.6923 0.01704 0.01144 -0.1173 0.2012 1.0000
11.250 1.6994 0.01797 0.01231 -0.1145 0.1877 1.0000
11.500 1.7066 0.01894 0.01323 -0.1119 0.1768 1.0000
11.750 1.7114 0.02007 0.01432 -0.1092 0.1649 1.0000
12.000 1.7163 0.02126 0.01548 -0.1066 0.1543 1.0000
12.250 1.7203 0.02257 0.01677 -0.1041 0.1438 1.0000
12.500 1.7239 0.02398 0.01816 -0.1017 0.1353 1.0000
12.750 1.7235 0.02575 0.01990 -0.0992 0.1248 1.0000
13.000 1.7202 0.02784 0.02197 -0.0967 0.1133 1.0000
13.250 1.7194 0.02989 0.02401 -0.0947 0.1044 1.0000
13.500 1.7196 0.03199 0.02612 -0.0930 0.0977 1.0000
13.750 1.7170 0.03443 0.02857 -0.0914 0.0907 1.0000
14.000 1.7174 0.03674 0.03091 -0.0902 0.0852 1.0000
14.250 1.7126 0.03965 0.03383 -0.0889 0.0791 1.0000
14.500 1.7085 0.04262 0.03682 -0.0880 0.0727 1.0000
14.750 1.7032 0.04585 0.04008 -0.0872 0.0673 1.0000
15.000 1.6973 0.04929 0.04356 -0.0866 0.0622 1.0000
15.250 1.6922 0.05274 0.04705 -0.0862 0.0579 1.0000
15.500 1.6846 0.05662 0.05097 -0.0861 0.0534 1.0000
15.750 1.6785 0.06045 0.05484 -0.0861 0.0493 1.0000
16.250 1.6632 0.06882 0.06331 -0.0866 0.0417 1.0000
16.750 1.6498 0.07737 0.07197 -0.0878 0.0362 1.0000
17.000 1.6416 0.08199 0.07664 -0.0886 0.0334 1.0000
17.250 1.6356 0.08638 0.08109 -0.0895 0.0309 1.0000
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Polar data table (+)
Polar graphs
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