EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 561 AIRFOIL (e561-il) Reynolds number: 500,000 Max Cl/Cd: 104.2 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e561-il-500000-n5.txt Download as CSV file: xf-e561-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.5819 0.13682 0.13368 -0.0438 1.0000 0.0117
-17.500 -0.5988 0.12945 0.12620 -0.0473 1.0000 0.0117
-17.250 -0.6086 0.12376 0.12042 -0.0499 1.0000 0.0117
-17.000 -0.6181 0.11828 0.11486 -0.0524 1.0000 0.0118
-16.750 -0.6247 0.11349 0.11000 -0.0545 1.0000 0.0118
-16.500 -0.6312 0.10878 0.10522 -0.0566 1.0000 0.0119
-16.250 -0.6373 0.10426 0.10063 -0.0586 1.0000 0.0119
-16.000 -0.6420 0.10009 0.09640 -0.0603 1.0000 0.0120
-15.750 -0.6485 0.09564 0.09188 -0.0622 1.0000 0.0121
-15.500 -0.6518 0.09190 0.08809 -0.0636 1.0000 0.0121
-15.250 -0.6551 0.08831 0.08446 -0.0650 1.0000 0.0121
-15.000 -0.6605 0.08436 0.08044 -0.0665 1.0000 0.0122
-14.750 -0.6639 0.08093 0.07698 -0.0676 1.0000 0.0122
-14.500 -0.6689 0.07727 0.07326 -0.0689 1.0000 0.0123
-14.250 -0.6741 0.07377 0.06971 -0.0700 1.0000 0.0123
-14.000 -0.6791 0.07044 0.06635 -0.0709 1.0000 0.0123
-13.750 -0.6859 0.06694 0.06279 -0.0719 1.0000 0.0124
-13.500 -0.6782 0.06300 0.05878 -0.0763 0.9985 0.0124
-13.250 -0.6735 0.05876 0.05450 -0.0810 0.9963 0.0126
-13.000 -0.6676 0.05464 0.05031 -0.0860 0.9940 0.0127
-12.750 -0.6661 0.05029 0.04590 -0.0907 0.9907 0.0128
-12.500 -0.6630 0.04598 0.04153 -0.0958 0.9866 0.0130
-12.250 -0.6542 0.04174 0.03720 -0.1018 0.9830 0.0131
-12.000 -0.6582 0.03776 0.03315 -0.1050 0.9741 0.0132
-11.750 -0.6656 0.03377 0.02908 -0.1078 0.9610 0.0133
-11.500 -0.6655 0.02953 0.02472 -0.1120 0.9447 0.0133
-11.250 -0.6443 0.02525 0.02028 -0.1202 0.9335 0.0136
-11.000 -0.6178 0.02306 0.01794 -0.1245 0.9232 0.0138
-10.750 -0.5821 0.02136 0.01612 -0.1291 0.9161 0.0141
-10.500 -0.5427 0.01996 0.01460 -0.1336 0.9068 0.0145
-10.250 -0.4933 0.01870 0.01320 -0.1398 0.8979 0.0149
-10.000 -0.4400 0.01764 0.01198 -0.1464 0.8858 0.0153
-9.750 -0.3976 0.01658 0.01077 -0.1509 0.8668 0.0159
-9.500 -0.3649 0.01591 0.00995 -0.1529 0.8454 0.0165
-9.250 -0.3373 0.01540 0.00928 -0.1535 0.8248 0.0171
-9.000 -0.3118 0.01498 0.00871 -0.1536 0.8058 0.0177
-8.750 -0.2869 0.01461 0.00820 -0.1534 0.7884 0.0184
-8.500 -0.2624 0.01419 0.00766 -0.1532 0.7722 0.0195
-8.250 -0.2377 0.01383 0.00719 -0.1529 0.7569 0.0212
-8.000 -0.2129 0.01345 0.00672 -0.1527 0.7428 0.0241
-7.750 -0.1879 0.01304 0.00626 -0.1525 0.7292 0.0303
-7.500 -0.1626 0.01259 0.00580 -0.1524 0.7161 0.0423
-7.250 -0.1370 0.01220 0.00539 -0.1523 0.7036 0.0557
-7.000 -0.1112 0.01187 0.00504 -0.1521 0.6917 0.0697
-6.750 -0.0846 0.01156 0.00473 -0.1521 0.6804 0.0839
-6.500 -0.0579 0.01130 0.00446 -0.1520 0.6697 0.0980
-6.250 -0.0313 0.01108 0.00423 -0.1519 0.6582 0.1140
-6.000 -0.0041 0.01087 0.00402 -0.1519 0.6475 0.1306
-5.750 0.0229 0.01071 0.00385 -0.1518 0.6376 0.1458
-5.500 0.0506 0.01059 0.00370 -0.1517 0.6281 0.1580
-5.250 0.0779 0.01048 0.00356 -0.1516 0.6189 0.1694
-5.000 0.1056 0.01039 0.00345 -0.1516 0.6092 0.1804
-4.750 0.1330 0.01032 0.00335 -0.1515 0.6000 0.1930
-4.500 0.1608 0.01027 0.00326 -0.1514 0.5908 0.2050
-4.250 0.1885 0.01022 0.00318 -0.1513 0.5831 0.2138
-4.000 0.2164 0.01020 0.00311 -0.1512 0.5748 0.2212
-3.750 0.2440 0.01017 0.00304 -0.1511 0.5670 0.2283
-3.500 0.2720 0.01015 0.00298 -0.1510 0.5586 0.2358
-3.250 0.2994 0.01016 0.00293 -0.1508 0.5509 0.2423
-3.000 0.3276 0.01014 0.00289 -0.1508 0.5438 0.2501
-2.750 0.3553 0.01016 0.00286 -0.1507 0.5367 0.2569
-2.500 0.3832 0.01015 0.00284 -0.1506 0.5301 0.2646
-2.250 0.4110 0.01018 0.00282 -0.1505 0.5228 0.2715
-2.000 0.4384 0.01020 0.00281 -0.1503 0.5160 0.2787
-1.750 0.4665 0.01022 0.00281 -0.1503 0.5098 0.2863
-1.500 0.4942 0.01025 0.00281 -0.1501 0.5037 0.2925
-1.250 0.5216 0.01029 0.00283 -0.1500 0.4979 0.3002
-1.000 0.5496 0.01033 0.00284 -0.1499 0.4919 0.3072
-0.750 0.5770 0.01037 0.00288 -0.1497 0.4857 0.3141
-0.500 0.6044 0.01043 0.00291 -0.1495 0.4805 0.3214
-0.250 0.6323 0.01047 0.00295 -0.1495 0.4754 0.3286
0.000 0.6596 0.01053 0.00300 -0.1493 0.4699 0.3359
0.500 0.7143 0.01065 0.00311 -0.1489 0.4599 0.3501
0.750 0.7416 0.01072 0.00317 -0.1488 0.4549 0.3576
1.000 0.7684 0.01081 0.00324 -0.1485 0.4503 0.3642
1.250 0.7955 0.01089 0.00333 -0.1483 0.4459 0.3721
1.500 0.8228 0.01096 0.00340 -0.1481 0.4412 0.3794
1.750 0.8496 0.01104 0.00349 -0.1479 0.4366 0.3869
2.000 0.8760 0.01115 0.00359 -0.1476 0.4325 0.3949
2.250 0.9029 0.01123 0.00370 -0.1473 0.4286 0.4028
2.500 0.9299 0.01131 0.00380 -0.1471 0.4243 0.4112
2.750 0.9563 0.01141 0.00392 -0.1468 0.4199 0.4193
3.000 0.9822 0.01153 0.00404 -0.1464 0.4160 0.4290
3.250 1.0084 0.01164 0.00417 -0.1461 0.4124 0.4380
3.500 1.0350 0.01173 0.00431 -0.1458 0.4085 0.4481
3.750 1.0611 0.01183 0.00445 -0.1455 0.4044 0.4593
4.250 1.1115 0.01211 0.00477 -0.1445 0.3968 0.4837
4.500 1.1378 0.01219 0.00492 -0.1442 0.3932 0.4982
4.750 1.1633 0.01230 0.00509 -0.1438 0.3893 0.5145
5.000 1.1882 0.01244 0.00528 -0.1432 0.3853 0.5322
5.250 1.2120 0.01260 0.00548 -0.1425 0.3814 0.5532
5.500 1.2370 0.01270 0.00568 -0.1420 0.3781 0.5777
5.750 1.2615 0.01280 0.00588 -0.1414 0.3743 0.6055
6.000 1.2848 0.01291 0.00610 -0.1406 0.3702 0.6390
6.250 1.3069 0.01305 0.00634 -0.1396 0.3663 0.6807
6.500 1.3292 0.01316 0.00660 -0.1386 0.3628 0.7319
6.750 1.3503 0.01319 0.00685 -0.1372 0.3590 0.8045
7.000 1.3640 0.01309 0.00700 -0.1342 0.3551 1.0000
7.250 1.3856 0.01334 0.00724 -0.1332 0.3509 1.0000
7.500 1.4072 0.01361 0.00750 -0.1321 0.3470 1.0000
7.750 1.4300 0.01382 0.00775 -0.1313 0.3429 1.0000
8.000 1.4514 0.01408 0.00803 -0.1302 0.3383 1.0000
8.250 1.4710 0.01440 0.00833 -0.1289 0.3337 1.0000
8.500 1.4919 0.01468 0.00863 -0.1278 0.3294 1.0000
8.750 1.5127 0.01496 0.00895 -0.1267 0.3242 1.0000
9.000 1.5309 0.01532 0.00931 -0.1252 0.3187 1.0000
9.250 1.5497 0.01568 0.00968 -0.1238 0.3135 1.0000
9.500 1.5686 0.01604 0.01006 -0.1225 0.3073 1.0000
9.750 1.5841 0.01652 0.01054 -0.1206 0.3012 1.0000
10.000 1.6024 0.01691 0.01097 -0.1193 0.2954 1.0000
10.250 1.6181 0.01740 0.01148 -0.1176 0.2889 1.0000
10.500 1.6327 0.01797 0.01204 -0.1158 0.2828 1.0000
10.750 1.6478 0.01852 0.01262 -0.1141 0.2757 1.0000
11.000 1.6592 0.01925 0.01335 -0.1120 0.2684 1.0000
11.250 1.6718 0.01996 0.01408 -0.1101 0.2594 1.0000
11.500 1.6808 0.02087 0.01498 -0.1079 0.2499 1.0000
11.750 1.6874 0.02196 0.01605 -0.1055 0.2398 1.0000
12.000 1.6944 0.02310 0.01718 -0.1034 0.2285 1.0000
12.250 1.6995 0.02441 0.01849 -0.1011 0.2182 1.0000
12.500 1.7009 0.02604 0.02009 -0.0988 0.2065 1.0000
12.750 1.7015 0.02783 0.02185 -0.0966 0.1954 1.0000
13.000 1.7045 0.02955 0.02360 -0.0948 0.1858 1.0000
13.250 1.7043 0.03161 0.02566 -0.0930 0.1767 1.0000
13.500 1.7016 0.03400 0.02805 -0.0913 0.1670 1.0000
13.750 1.6992 0.03650 0.03056 -0.0898 0.1569 1.0000
14.000 1.6959 0.03921 0.03329 -0.0885 0.1488 1.0000
14.250 1.6897 0.04232 0.03641 -0.0874 0.1401 1.0000
14.500 1.6852 0.04541 0.03954 -0.0866 0.1321 1.0000
14.750 1.6777 0.04894 0.04309 -0.0859 0.1246 1.0000
15.000 1.6708 0.05254 0.04673 -0.0855 0.1171 1.0000
15.250 1.6627 0.05643 0.05065 -0.0852 0.1105 1.0000
15.500 1.6534 0.06060 0.05486 -0.0852 0.1037 1.0000
15.750 1.6447 0.06481 0.05912 -0.0853 0.0972 1.0000
16.000 1.6333 0.06951 0.06385 -0.0857 0.0907 1.0000
16.250 1.6267 0.07370 0.06810 -0.0862 0.0856 1.0000
16.500 1.6158 0.07856 0.07299 -0.0869 0.0800 1.0000
16.750 1.6080 0.08309 0.07758 -0.0877 0.0748 1.0000
17.000 1.5978 0.08808 0.08261 -0.0888 0.0699 1.0000
17.250 1.5907 0.09267 0.08726 -0.0898 0.0652 1.0000
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