NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M27 AIRFOIL (m27-il) Reynolds number: 100,000 Max Cl/Cd: 41.3 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m27-il-100000-n5.txt Download as CSV file: xf-m27-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M27 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1431 0.10540 0.09995 -0.0256 0.6399 0.0432
-8.000 -0.1391 0.10348 0.09800 -0.0291 0.6369 0.0437
-7.750 -0.1379 0.10200 0.09650 -0.0325 0.6336 0.0439
-7.500 -0.1302 0.10035 0.09483 -0.0371 0.6294 0.0440
-7.250 -0.1181 0.09512 0.08962 -0.0357 0.6253 0.0445
-7.000 -0.1072 0.09131 0.08577 -0.0351 0.6218 0.0453
-6.750 -0.0968 0.08845 0.08284 -0.0358 0.6189 0.0467
-6.500 -0.0843 0.08582 0.08020 -0.0379 0.6146 0.0484
-6.250 -0.0704 0.08333 0.07768 -0.0405 0.6107 0.0504
-6.000 -0.0523 0.08159 0.07582 -0.0450 0.6072 0.0519
-5.750 -0.0299 0.08054 0.07454 -0.0501 0.6043 0.0525
-5.500 -0.0158 0.07674 0.07070 -0.0507 0.6011 0.0528
-5.250 -0.0038 0.07283 0.06685 -0.0502 0.5968 0.0536
-5.000 0.0112 0.06995 0.06393 -0.0505 0.5929 0.0549
-4.750 0.0293 0.06754 0.06142 -0.0516 0.5897 0.0573
-4.500 0.0552 0.06597 0.05963 -0.0542 0.5870 0.0609
-4.250 0.0914 0.06602 0.05933 -0.0585 0.5832 0.0620
-4.000 0.1059 0.06200 0.05535 -0.0586 0.5792 0.0625
-3.750 0.1205 0.05867 0.05202 -0.0583 0.5757 0.0634
-3.500 0.1390 0.05618 0.04942 -0.0583 0.5727 0.0648
-3.250 0.1605 0.05408 0.04716 -0.0587 0.5702 0.0667
-3.000 0.1883 0.05286 0.04582 -0.0601 0.5659 0.0713
-2.750 0.2240 0.05262 0.04521 -0.0619 0.5621 0.0737
-2.500 0.2402 0.04930 0.04189 -0.0617 0.5589 0.0747
-2.250 0.2602 0.04701 0.03950 -0.0615 0.5561 0.0760
-2.000 0.2830 0.04519 0.03751 -0.0614 0.5537 0.0779
-1.750 0.3077 0.04382 0.03608 -0.0618 0.5492 0.0802
-1.500 0.3347 0.04265 0.03473 -0.0621 0.5454 0.0834
-1.250 0.3715 0.04324 0.03483 -0.0625 0.5423 0.0867
-1.000 0.3917 0.04031 0.03184 -0.0623 0.5399 0.0879
-0.750 0.4126 0.03831 0.02976 -0.0620 0.5376 0.0906
-0.250 0.4706 0.03499 0.02592 -0.0616 0.5296 0.0604
0.000 0.4964 0.03370 0.02446 -0.0614 0.5265 0.0581
0.250 0.5245 0.03232 0.02278 -0.0610 0.5241 0.0556
0.750 0.5821 0.02983 0.01961 -0.0604 0.5182 0.0526
1.000 0.6066 0.02949 0.01931 -0.0605 0.5142 0.0544
1.250 0.6334 0.02896 0.01864 -0.0604 0.5110 0.0562
1.500 0.6621 0.02815 0.01760 -0.0604 0.5084 0.0567
1.750 0.6916 0.02735 0.01655 -0.0603 0.5063 0.0569
2.000 0.7181 0.02709 0.01622 -0.0605 0.5027 0.0575
2.250 0.7446 0.02690 0.01597 -0.0607 0.4988 0.0586
2.500 0.7729 0.02658 0.01554 -0.0609 0.4956 0.0602
2.750 0.8064 0.02632 0.01520 -0.0621 0.4929 0.0644
3.000 0.8379 0.02605 0.01482 -0.0627 0.4907 0.0696
3.250 0.8614 0.02624 0.01496 -0.0625 0.4872 0.0735
3.500 0.8809 0.02661 0.01542 -0.0617 0.4834 0.0791
3.750 0.9022 0.02676 0.01554 -0.0609 0.4802 0.0903
4.000 0.9253 0.02677 0.01553 -0.0603 0.4776 0.1177
4.250 0.9501 0.02669 0.01550 -0.0598 0.4755 0.1679
4.500 1.0724 0.02621 0.01641 -0.0803 0.4709 1.0000
4.750 1.0891 0.02703 0.01724 -0.0792 0.4671 1.0000
5.000 1.1085 0.02753 0.01771 -0.0783 0.4641 1.0000
5.250 1.1301 0.02782 0.01792 -0.0775 0.4617 1.0000
5.500 1.1538 0.02794 0.01795 -0.0769 0.4597 1.0000
5.750 1.1722 0.02850 0.01850 -0.0759 0.4568 1.0000
6.000 1.1774 0.02999 0.02013 -0.0737 0.4520 1.0000
6.250 1.1910 0.03080 0.02096 -0.0722 0.4489 1.0000
6.500 1.2093 0.03124 0.02141 -0.0711 0.4465 1.0000
6.750 1.2318 0.03142 0.02154 -0.0704 0.4445 1.0000
7.000 1.2580 0.03140 0.02146 -0.0700 0.4429 1.0000
7.250 1.2207 0.03511 0.02547 -0.0637 0.4355 1.0000
7.500 1.2232 0.03638 0.02677 -0.0611 0.4321 1.0000
7.750 1.2395 0.03682 0.02722 -0.0597 0.4300 1.0000
8.000 1.2639 0.03686 0.02726 -0.0592 0.4285 1.0000
8.250 1.2859 0.03708 0.02747 -0.0584 0.4268 1.0000
8.750 1.1820 0.04770 0.03829 -0.0474 0.4114 1.0000
10.250 0.9936 0.08704 0.07807 -0.0421 0.3556 1.0000
10.500 1.0088 0.08806 0.07914 -0.0416 0.3537 1.0000
10.750 1.0268 0.08866 0.07976 -0.0410 0.3523 1.0000
11.000 1.0471 0.08892 0.08006 -0.0405 0.3512 1.0000
11.500 1.0238 0.09837 0.08964 -0.0406 0.3380 1.0000
11.750 1.0425 0.09885 0.09018 -0.0401 0.3366 1.0000
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Polar data table (+)
Polar graphs
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