Dormoy (dormoy-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 500,000 Max Cl/Cd: 62.79 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dormoy-il-500000-n5.txt Download as CSV file: xf-dormoy-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3740 0.08807 0.08598 -0.0302 1.0000 0.0043
-9.500 -0.3732 0.08482 0.08276 -0.0312 1.0000 0.0043
-9.250 -0.3745 0.08148 0.07946 -0.0321 1.0000 0.0043
-9.000 -0.3787 0.07844 0.07647 -0.0326 1.0000 0.0043
-8.750 -0.3786 0.07449 0.07256 -0.0358 0.9969 0.0043
-8.500 -0.3609 0.06863 0.06667 -0.0441 0.9851 0.0043
-8.250 -0.3369 0.06156 0.05954 -0.0536 0.9702 0.0043
-8.000 -0.3078 0.05466 0.05249 -0.0624 0.9540 0.0043
-7.750 -0.2796 0.04741 0.04502 -0.0701 0.9310 0.0044
-7.500 -0.2556 0.04132 0.03862 -0.0754 0.8973 0.0045
-7.250 -0.2390 0.03756 0.03451 -0.0765 0.8624 0.0046
-7.000 -0.2247 0.03455 0.03122 -0.0762 0.8422 0.0048
-6.750 -0.2083 0.03154 0.02789 -0.0755 0.8280 0.0048
-6.500 -0.1908 0.02885 0.02486 -0.0746 0.8156 0.0051
-6.250 -0.1715 0.02619 0.02186 -0.0735 0.8045 0.0052
-6.000 -0.1508 0.02375 0.01906 -0.0722 0.7937 0.0054
-5.000 -0.0556 0.01698 0.01101 -0.0677 0.7571 0.0065
-4.750 -0.0310 0.01516 0.00890 -0.0666 0.7477 0.0057
-4.500 -0.0052 0.01373 0.00724 -0.0656 0.7364 0.0051
-4.250 0.0204 0.01256 0.00588 -0.0646 0.7246 0.0049
-4.000 0.0452 0.01168 0.00487 -0.0637 0.7099 0.0049
-3.750 0.0694 0.01099 0.00405 -0.0628 0.6921 0.0050
-3.500 0.0936 0.01048 0.00338 -0.0619 0.6704 0.0055
-3.000 0.1412 0.00982 0.00234 -0.0601 0.6083 0.0085
-2.750 0.1641 0.00975 0.00196 -0.0590 0.5562 0.0099
-2.500 0.1874 0.00987 0.00173 -0.0582 0.4974 0.0130
-2.250 0.2112 0.00999 0.00151 -0.0573 0.4377 0.0184
-2.000 0.2318 0.00990 0.00148 -0.0563 0.3612 0.1625
-1.750 0.2559 0.00994 0.00146 -0.0559 0.3285 0.2040
-1.500 0.2783 0.00953 0.00147 -0.0553 0.3082 0.3798
-1.250 0.2990 0.00910 0.00151 -0.0542 0.2859 0.5628
-1.000 0.3208 0.00894 0.00155 -0.0532 0.2587 0.6693
-0.750 0.3377 0.00920 0.00173 -0.0512 0.1649 0.7724
-0.500 0.3609 0.00906 0.00185 -0.0500 0.1541 0.8840
-0.250 0.4126 0.00920 0.00199 -0.0554 0.1445 0.9578
0.000 0.4511 0.00939 0.00208 -0.0580 0.1322 0.9784
0.250 0.4858 0.00981 0.00224 -0.0600 0.0685 0.9902
0.500 0.5211 0.01002 0.00239 -0.0619 0.0602 1.0000
0.750 0.5449 0.01017 0.00253 -0.0612 0.0574 1.0000
1.000 0.5689 0.01032 0.00267 -0.0606 0.0565 1.0000
1.250 0.5928 0.01047 0.00283 -0.0600 0.0555 1.0000
1.500 0.6168 0.01063 0.00302 -0.0593 0.0548 1.0000
1.750 0.6407 0.01080 0.00321 -0.0587 0.0540 1.0000
2.000 0.6646 0.01100 0.00343 -0.0581 0.0520 1.0000
2.250 0.6876 0.01128 0.00374 -0.0573 0.0457 1.0000
2.500 0.7123 0.01139 0.00379 -0.0570 0.0369 1.0000
2.750 0.7353 0.01171 0.00407 -0.0562 0.0113 1.0000
3.000 0.7579 0.01212 0.00461 -0.0552 0.0076 1.0000
3.250 0.7810 0.01248 0.00506 -0.0544 0.0065 1.0000
3.500 0.8029 0.01295 0.00561 -0.0535 0.0049 1.0000
3.750 0.8244 0.01350 0.00625 -0.0524 0.0043 1.0000
4.000 0.8449 0.01416 0.00700 -0.0511 0.0039 1.0000
4.250 0.8639 0.01496 0.00789 -0.0496 0.0036 1.0000
4.500 0.8816 0.01586 0.00888 -0.0479 0.0035 1.0000
4.750 0.8976 0.01690 0.01005 -0.0460 0.0034 1.0000
5.000 0.9131 0.01801 0.01126 -0.0439 0.0034 1.0000
5.250 0.9267 0.01929 0.01255 -0.0421 0.0028 1.0000
5.500 0.9456 0.02015 0.01355 -0.0406 0.0025 1.0000
5.750 0.9627 0.02152 0.01506 -0.0387 0.0020 1.0000
6.000 0.9806 0.02309 0.01674 -0.0372 0.0020 1.0000
6.250 1.0000 0.02497 0.01877 -0.0358 0.0019 1.0000
6.500 1.0199 0.02708 0.02105 -0.0346 0.0018 1.0000
6.750 1.0397 0.02970 0.02391 -0.0332 0.0020 1.0000
7.000 1.0566 0.03262 0.02710 -0.0314 0.0020 1.0000
7.250 1.0699 0.03553 0.03031 -0.0294 0.0022 1.0000
7.500 1.0779 0.03866 0.03370 -0.0270 0.0024 1.0000
7.750 1.0807 0.04167 0.03693 -0.0245 0.0026 1.0000
13.250 0.6890 0.14842 0.14654 -0.0494 0.0047 1.0000
13.500 0.6884 0.15372 0.15185 -0.0518 0.0046 1.0000
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Polar data table (+)
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