EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 550 AIRFOIL (e550-il) Reynolds number: 1,000,000 Max Cl/Cd: 124.41 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e550-il-1000000.txt Download as CSV file: xf-e550-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 550 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.6637 0.11225 0.11018 -0.0348 1.0000 0.0050
-16.250 -0.7141 0.09639 0.09409 -0.0435 1.0000 0.0048
-16.000 -0.7569 0.08386 0.08129 -0.0505 1.0000 0.0047
-15.750 -0.7749 0.07688 0.07417 -0.0542 1.0000 0.0047
-15.500 -0.7959 0.07003 0.06713 -0.0574 1.0000 0.0046
-15.250 -0.8198 0.06330 0.06018 -0.0601 1.0000 0.0046
-15.000 -0.8350 0.05824 0.05495 -0.0616 1.0000 0.0046
-14.750 -0.8475 0.05383 0.05036 -0.0626 1.0000 0.0045
-14.500 -0.8556 0.05020 0.04657 -0.0631 1.0000 0.0045
-14.250 -0.8608 0.04705 0.04329 -0.0632 1.0000 0.0045
-14.000 -0.8646 0.04424 0.04035 -0.0630 1.0000 0.0045
-13.750 -0.8669 0.04167 0.03767 -0.0626 1.0000 0.0046
-13.500 -0.8666 0.03944 0.03533 -0.0621 1.0000 0.0046
-13.250 -0.8651 0.03737 0.03315 -0.0614 1.0000 0.0046
-13.000 -0.8633 0.03539 0.03106 -0.0605 1.0000 0.0046
-12.750 -0.8589 0.03369 0.02928 -0.0595 1.0000 0.0046
-12.500 -0.8530 0.03218 0.02770 -0.0585 1.0000 0.0046
-12.250 -0.8487 0.03057 0.02600 -0.0573 1.0000 0.0047
-12.000 -0.8420 0.02921 0.02457 -0.0561 1.0000 0.0047
-11.750 -0.8360 0.02786 0.02315 -0.0546 1.0000 0.0047
-11.500 -0.8281 0.02672 0.02196 -0.0532 1.0000 0.0051
-11.250 -0.8000 0.02520 0.02036 -0.0560 0.9974 0.0051
-11.000 -0.7875 0.02386 0.01896 -0.0554 0.9640 0.0049
-10.750 -0.7007 0.02218 0.01714 -0.0695 0.9346 0.0054
-10.500 -0.6131 0.01998 0.01458 -0.0854 0.8656 0.0062
-10.250 -0.6055 0.01929 0.01360 -0.0832 0.8098 0.0061
-10.000 -0.5957 0.01864 0.01280 -0.0814 0.7786 0.0063
-9.750 -0.5853 0.01796 0.01200 -0.0796 0.7550 0.0064
-9.500 -0.5731 0.01736 0.01130 -0.0780 0.7351 0.0068
-9.250 -0.5619 0.01671 0.01055 -0.0763 0.7181 0.0070
-9.000 -0.5519 0.01605 0.00980 -0.0743 0.7032 0.0071
-8.750 -0.5424 0.01549 0.00914 -0.0721 0.6894 0.0073
-8.250 -0.5263 0.01439 0.00788 -0.0667 0.6652 0.0080
-8.000 -0.5095 0.01398 0.00740 -0.0653 0.6541 0.0085
-7.500 -0.4705 0.01328 0.00658 -0.0631 0.6338 0.0098
-7.250 -0.4512 0.01287 0.00611 -0.0620 0.6249 0.0112
-7.000 -0.4295 0.01252 0.00572 -0.0613 0.6163 0.0129
-6.750 -0.4078 0.01218 0.00535 -0.0605 0.6084 0.0162
-6.500 -0.3853 0.01181 0.00499 -0.0599 0.6008 0.0233
-6.250 -0.3629 0.01147 0.00467 -0.0593 0.5933 0.0341
-6.000 -0.3394 0.01108 0.00435 -0.0589 0.5868 0.0498
-5.750 -0.3160 0.01072 0.00406 -0.0585 0.5799 0.0713
-5.500 -0.2925 0.01030 0.00375 -0.0581 0.5739 0.1033
-5.250 -0.2693 0.00977 0.00342 -0.0578 0.5678 0.1516
-5.000 -0.2473 0.00910 0.00302 -0.0575 0.5621 0.2284
-4.750 -0.2268 0.00800 0.00245 -0.0571 0.5575 0.3649
-4.500 -0.2033 0.00725 0.00218 -0.0570 0.5527 0.4967
-4.250 -0.1748 0.00726 0.00217 -0.0572 0.5478 0.5231
-4.000 -0.1459 0.00732 0.00218 -0.0574 0.5432 0.5359
-3.750 -0.1168 0.00732 0.00217 -0.0576 0.5392 0.5430
-3.500 -0.0876 0.00739 0.00217 -0.0579 0.5348 0.5504
-3.250 -0.0589 0.00745 0.00217 -0.0581 0.5305 0.5567
-3.000 -0.0299 0.00753 0.00222 -0.0583 0.5267 0.5628
-2.750 -0.0004 0.00763 0.00227 -0.0586 0.5236 0.5701
-2.500 0.0285 0.00775 0.00242 -0.0587 0.5201 0.5790
-2.250 0.0575 0.00786 0.00246 -0.0589 0.5167 0.5832
-2.000 0.0863 0.00792 0.00244 -0.0592 0.5132 0.5845
-1.750 0.1155 0.00792 0.00240 -0.0595 0.5103 0.5856
-1.500 0.1446 0.00786 0.00233 -0.0598 0.5076 0.5872
-1.250 0.1737 0.00784 0.00230 -0.0601 0.5047 0.5887
-1.000 0.2027 0.00785 0.00228 -0.0604 0.5018 0.5901
-0.750 0.2315 0.00789 0.00228 -0.0607 0.4990 0.5915
-0.500 0.2600 0.00795 0.00231 -0.0609 0.4957 0.5928
-0.250 0.2893 0.00796 0.00231 -0.0612 0.4938 0.5941
0.000 0.3185 0.00796 0.00231 -0.0616 0.4915 0.5954
0.250 0.3477 0.00798 0.00231 -0.0619 0.4891 0.5967
0.500 0.3767 0.00801 0.00233 -0.0622 0.4867 0.5981
0.750 0.4055 0.00806 0.00235 -0.0625 0.4843 0.5995
1.000 0.4341 0.00814 0.00239 -0.0628 0.4815 0.6006
1.250 0.4628 0.00822 0.00244 -0.0630 0.4789 0.6016
1.500 0.4918 0.00819 0.00244 -0.0634 0.4771 0.6034
1.750 0.5207 0.00819 0.00246 -0.0637 0.4751 0.6050
2.000 0.5495 0.00821 0.00250 -0.0640 0.4728 0.6065
2.250 0.5782 0.00824 0.00254 -0.0643 0.4704 0.6080
2.500 0.6068 0.00830 0.00259 -0.0645 0.4680 0.6095
2.750 0.6350 0.00840 0.00267 -0.0647 0.4650 0.6110
3.000 0.6635 0.00847 0.00275 -0.0650 0.4625 0.6127
3.250 0.6923 0.00849 0.00280 -0.0653 0.4602 0.6144
3.500 0.7210 0.00852 0.00285 -0.0655 0.4575 0.6160
3.750 0.7495 0.00857 0.00291 -0.0658 0.4547 0.6174
4.000 0.7777 0.00863 0.00297 -0.0660 0.4518 0.6187
4.250 0.8053 0.00872 0.00306 -0.0661 0.4484 0.6210
4.500 0.8336 0.00875 0.00313 -0.0664 0.4458 0.6229
4.750 0.8620 0.00877 0.00321 -0.0666 0.4430 0.6248
5.000 0.8903 0.00881 0.00328 -0.0668 0.4397 0.6267
5.250 0.9180 0.00887 0.00336 -0.0670 0.4362 0.6286
5.500 0.9450 0.00901 0.00348 -0.0670 0.4319 0.6306
5.750 0.9734 0.00904 0.00357 -0.0672 0.4289 0.6326
6.000 1.0015 0.00908 0.00366 -0.0674 0.4251 0.6344
6.250 1.0289 0.00914 0.00374 -0.0675 0.4208 0.6369
6.500 1.0552 0.00926 0.00387 -0.0674 0.4160 0.6396
6.750 1.0833 0.00928 0.00397 -0.0676 0.4119 0.6420
7.000 1.1105 0.00935 0.00408 -0.0677 0.4061 0.6445
7.250 1.1365 0.00949 0.00422 -0.0676 0.4002 0.6470
7.500 1.1640 0.00955 0.00434 -0.0677 0.3934 0.6494
7.750 1.1893 0.00971 0.00448 -0.0674 0.3850 0.6516
8.000 1.2157 0.00980 0.00463 -0.0674 0.3756 0.6550
8.250 1.2404 0.00997 0.00482 -0.0671 0.3635 0.6581
8.500 1.2637 0.01022 0.00504 -0.0665 0.3474 0.6613
8.750 1.2852 0.01057 0.00533 -0.0657 0.3281 0.6645
9.000 1.3038 0.01105 0.00571 -0.0644 0.3031 0.6677
9.250 1.3194 0.01164 0.00618 -0.0626 0.2757 0.6717
9.500 1.3337 0.01225 0.00670 -0.0606 0.2511 0.6758
9.750 1.3476 0.01284 0.00721 -0.0586 0.2294 0.6800
10.000 1.3576 0.01345 0.00774 -0.0558 0.2093 0.6840
10.250 1.3640 0.01406 0.00830 -0.0525 0.1918 0.6886
10.500 1.3698 0.01475 0.00894 -0.0491 0.1748 0.6937
10.750 1.3743 0.01551 0.00965 -0.0458 0.1584 0.6991
11.000 1.3779 0.01633 0.01044 -0.0425 0.1443 0.7048
11.250 1.3796 0.01727 0.01136 -0.0392 0.1316 0.7116
11.750 1.3818 0.01951 0.01362 -0.0334 0.1106 0.7269
12.000 1.3820 0.02090 0.01502 -0.0310 0.1015 0.7361
12.250 1.3795 0.02259 0.01673 -0.0287 0.0920 0.7472
12.500 1.3796 0.02428 0.01848 -0.0269 0.0852 0.7600
12.750 1.3764 0.02633 0.02057 -0.0252 0.0764 0.7758
13.000 1.3748 0.02837 0.02269 -0.0238 0.0707 0.7961
13.250 1.3726 0.03048 0.02490 -0.0225 0.0648 0.8252
13.500 1.3670 0.03250 0.02724 -0.0206 0.0592 0.9320
13.750 1.3680 0.03524 0.03000 -0.0211 0.0529 1.0000
14.000 1.3666 0.03774 0.03253 -0.0205 0.0479 1.0000
14.250 1.3637 0.04044 0.03523 -0.0201 0.0441 1.0000
14.500 1.3624 0.04306 0.03788 -0.0198 0.0399 1.0000
14.750 1.3596 0.04592 0.04076 -0.0196 0.0366 1.0000
15.000 1.3599 0.04856 0.04343 -0.0196 0.0335 1.0000
15.250 1.3574 0.05155 0.04644 -0.0197 0.0305 1.0000
15.500 1.3598 0.05410 0.04903 -0.0198 0.0287 1.0000
15.750 1.3566 0.05731 0.05225 -0.0201 0.0255 1.0000
16.000 1.3583 0.06005 0.05504 -0.0205 0.0239 1.0000
16.250 1.3585 0.06300 0.05803 -0.0209 0.0219 1.0000
16.500 1.3586 0.06606 0.06113 -0.0215 0.0204 1.0000
16.750 1.3595 0.06905 0.06416 -0.0221 0.0188 1.0000
17.000 1.3582 0.07236 0.06751 -0.0228 0.0173 1.0000
17.250 1.3592 0.07546 0.07066 -0.0236 0.0159 1.0000
17.500 1.3595 0.07870 0.07394 -0.0245 0.0149 1.0000
17.750 1.3582 0.08221 0.07750 -0.0255 0.0139 1.0000
18.000 1.3598 0.08535 0.08071 -0.0265 0.0129 1.0000
18.250 1.3586 0.08896 0.08436 -0.0276 0.0121 1.0000
18.500 1.3569 0.09267 0.08813 -0.0289 0.0112 1.0000
18.750 1.3570 0.09621 0.09174 -0.0302 0.0106 1.0000
19.000 1.3570 0.09976 0.09535 -0.0315 0.0099 1.0000
19.250 1.3531 0.10397 0.09962 -0.0332 0.0091 1.0000
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