Dormoy (dormoy-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.18 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dormoy-il-1000000-n5.txt Download as CSV file: xf-dormoy-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Dormoy
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3812 0.09406 0.09253 -0.0263 1.0000 0.0024
-10.000 -0.3785 0.09089 0.08938 -0.0273 1.0000 0.0024
-9.750 -0.3780 0.08727 0.08579 -0.0285 1.0000 0.0024
-9.500 -0.3741 0.08360 0.08213 -0.0304 0.9928 0.0024
-9.250 -0.3575 0.07825 0.07678 -0.0373 0.9722 0.0024
-9.000 -0.2938 0.06764 0.06602 -0.0617 0.9202 0.0024
-8.750 -0.2880 0.06307 0.06111 -0.0672 0.8439 0.0024
-6.750 -0.2119 0.03017 0.02684 -0.0747 0.7554 0.0021
-6.500 -0.1950 0.02691 0.02326 -0.0736 0.7468 0.0020
-6.250 -0.1758 0.02397 0.02001 -0.0723 0.7373 0.0019
-6.000 -0.1551 0.02116 0.01685 -0.0707 0.7275 0.0020
-5.750 -0.1325 0.01870 0.01402 -0.0690 0.7162 0.0021
-5.500 -0.1086 0.01660 0.01157 -0.0675 0.7035 0.0024
-5.250 -0.0856 0.01516 0.00985 -0.0666 0.6864 0.0027
-5.000 -0.0609 0.01486 0.00939 -0.0662 0.6652 0.0037
-4.750 -0.0361 0.01356 0.00781 -0.0652 0.6471 0.0036
-4.500 -0.0111 0.01235 0.00638 -0.0642 0.6268 0.0033
-4.250 0.0135 0.01127 0.00508 -0.0632 0.6005 0.0032
-4.000 0.0368 0.01045 0.00402 -0.0619 0.5618 0.0031
-3.750 0.0584 0.00999 0.00321 -0.0606 0.4926 0.0031
-3.500 0.0784 0.01002 0.00271 -0.0591 0.3715 0.0033
-3.250 0.1023 0.00989 0.00231 -0.0583 0.3253 0.0040
-3.000 0.1276 0.00967 0.00196 -0.0578 0.3071 0.0049
-2.750 0.1539 0.00963 0.00185 -0.0576 0.2932 0.0063
-2.500 0.1798 0.00959 0.00166 -0.0572 0.2730 0.0073
-2.250 0.2030 0.00980 0.00149 -0.0564 0.1887 0.0113
-2.000 0.2284 0.00993 0.00145 -0.0560 0.1587 0.0152
-1.750 0.2532 0.00960 0.00139 -0.0556 0.1527 0.1425
-1.500 0.2795 0.00959 0.00140 -0.0554 0.1469 0.1688
-1.250 0.3060 0.00957 0.00141 -0.0553 0.1417 0.1891
-1.000 0.3297 0.00923 0.00142 -0.0548 0.1324 0.3389
-0.750 0.3549 0.00916 0.00146 -0.0545 0.1199 0.4086
-0.250 0.4043 0.00930 0.00167 -0.0537 0.0554 0.5045
0.000 0.4289 0.00916 0.00176 -0.0532 0.0532 0.5906
0.250 0.4532 0.00903 0.00185 -0.0527 0.0515 0.6721
0.500 0.4760 0.00887 0.00195 -0.0518 0.0500 0.7633
0.750 0.4961 0.00863 0.00209 -0.0500 0.0484 0.8821
1.000 0.5424 0.00870 0.00232 -0.0543 0.0465 0.9656
1.250 0.5851 0.00888 0.00252 -0.0579 0.0455 0.9845
1.500 0.6218 0.00905 0.00270 -0.0602 0.0453 0.9944
1.750 0.6547 0.00917 0.00278 -0.0616 0.0439 1.0000
2.000 0.6791 0.00928 0.00287 -0.0611 0.0402 1.0000
2.250 0.7031 0.00944 0.00300 -0.0606 0.0339 1.0000
2.500 0.7254 0.00980 0.00330 -0.0596 0.0079 1.0000
2.750 0.7489 0.01003 0.00357 -0.0589 0.0058 1.0000
3.000 0.7719 0.01033 0.00392 -0.0581 0.0045 1.0000
3.250 0.7954 0.01058 0.00420 -0.0574 0.0035 1.0000
3.500 0.8176 0.01098 0.00465 -0.0565 0.0027 1.0000
3.750 0.8398 0.01141 0.00514 -0.0555 0.0025 1.0000
4.000 0.8608 0.01198 0.00579 -0.0543 0.0023 1.0000
4.250 0.8805 0.01268 0.00660 -0.0528 0.0021 1.0000
4.500 0.9008 0.01330 0.00728 -0.0516 0.0019 1.0000
4.750 0.9228 0.01369 0.00772 -0.0509 0.0016 1.0000
5.000 0.9387 0.01470 0.00884 -0.0489 0.0014 1.0000
5.250 0.9563 0.01555 0.00978 -0.0472 0.0013 1.0000
5.500 0.9712 0.01668 0.01102 -0.0451 0.0012 1.0000
5.750 0.9843 0.01826 0.01273 -0.0424 0.0009 1.0000
6.000 1.0004 0.01986 0.01443 -0.0404 0.0009 1.0000
6.250 1.0186 0.02170 0.01640 -0.0388 0.0008 1.0000
6.500 1.0380 0.02382 0.01868 -0.0374 0.0008 1.0000
6.750 1.0575 0.02664 0.02173 -0.0358 0.0009 1.0000
7.000 1.0743 0.02976 0.02514 -0.0339 0.0009 1.0000
7.250 1.0882 0.03277 0.02839 -0.0317 0.0010 1.0000
7.500 1.0980 0.03605 0.03192 -0.0292 0.0011 1.0000
7.750 1.1044 0.03901 0.03512 -0.0266 0.0012 1.0000
8.000 1.1039 0.04219 0.03852 -0.0234 0.0013 1.0000
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Polar data table (+)
Polar graphs
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