NACA M27 AIRFOIL (m27-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: NACA M27 AIRFOIL (m27-il) Reynolds number: 200,000 Max Cl/Cd: 70.12 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m27-il-200000-n5.txt Download as CSV file: xf-m27-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.1484 0.09594 0.09124 -0.0217 0.5886 0.0275
-7.500 -0.1414 0.09310 0.08836 -0.0239 0.5860 0.0283
-7.250 -0.1362 0.09083 0.08610 -0.0275 0.5828 0.0295
-7.000 -0.1246 0.08869 0.08391 -0.0335 0.5795 0.0299
-6.750 -0.1103 0.08601 0.08116 -0.0377 0.5763 0.0300
-6.500 -0.0978 0.08220 0.07731 -0.0386 0.5732 0.0301
-6.250 -0.0870 0.07851 0.07357 -0.0379 0.5704 0.0304
-6.000 -0.0734 0.07553 0.07059 -0.0387 0.5670 0.0309
-5.750 -0.0578 0.07281 0.06784 -0.0401 0.5637 0.0315
-5.500 -0.0407 0.07023 0.06521 -0.0418 0.5604 0.0325
-5.250 -0.0214 0.06768 0.06256 -0.0439 0.5574 0.0343
-5.000 0.0085 0.06566 0.06032 -0.0484 0.5547 0.0361
-4.750 0.0371 0.06344 0.05791 -0.0518 0.5515 0.0363
-4.500 0.0584 0.06036 0.05475 -0.0532 0.5481 0.0365
-4.250 0.0718 0.05699 0.05139 -0.0528 0.5448 0.0369
-4.000 0.0889 0.05447 0.04882 -0.0529 0.5419 0.0376
-3.750 0.1093 0.05239 0.04664 -0.0534 0.5392 0.0389
-3.500 0.1329 0.05038 0.04452 -0.0543 0.5364 0.0407
-3.250 0.1652 0.04873 0.04268 -0.0562 0.5329 0.0434
-3.000 0.1997 0.04724 0.04090 -0.0577 0.5296 0.0440
-2.750 0.2206 0.04440 0.03796 -0.0579 0.5266 0.0443
-2.500 0.2391 0.04204 0.03555 -0.0578 0.5239 0.0449
-2.250 0.2610 0.04026 0.03366 -0.0578 0.5215 0.0458
-2.000 0.2853 0.03877 0.03212 -0.0581 0.5182 0.0478
-1.750 0.3242 0.03828 0.03126 -0.0587 0.5149 0.0524
-1.500 0.3499 0.03628 0.02908 -0.0587 0.5119 0.0527
-1.250 0.3707 0.03404 0.02679 -0.0587 0.5090 0.0534
-1.000 0.3944 0.03253 0.02516 -0.0586 0.5065 0.0541
-0.750 0.4244 0.03010 0.02240 -0.0580 0.5038 0.0435
-0.500 0.4489 0.02874 0.02099 -0.0580 0.5008 0.0418
-0.250 0.4763 0.02728 0.01935 -0.0578 0.4978 0.0406
0.000 0.5043 0.02597 0.01783 -0.0576 0.4949 0.0415
0.250 0.5321 0.02459 0.01620 -0.0573 0.4923 0.0405
0.500 0.5608 0.02293 0.01420 -0.0569 0.4899 0.0390
0.750 0.5904 0.02109 0.01204 -0.0566 0.4869 0.0381
1.000 0.6195 0.01997 0.01069 -0.0567 0.4839 0.0381
1.250 0.6482 0.01926 0.00981 -0.0569 0.4810 0.0385
1.500 0.6767 0.01873 0.00914 -0.0570 0.4782 0.0391
1.750 0.7046 0.01842 0.00872 -0.0571 0.4757 0.0410
2.000 0.7325 0.01808 0.00826 -0.0572 0.4731 0.0425
2.250 0.7596 0.01778 0.00795 -0.0573 0.4698 0.0430
2.500 0.7861 0.01757 0.00772 -0.0572 0.4668 0.0437
2.750 0.8119 0.01738 0.00753 -0.0570 0.4641 0.0448
3.000 0.8379 0.01728 0.00744 -0.0568 0.4615 0.0465
3.250 0.8639 0.01724 0.00735 -0.0567 0.4592 0.0489
3.500 0.8896 0.01726 0.00740 -0.0566 0.4564 0.0532
3.750 0.9145 0.01731 0.00752 -0.0563 0.4532 0.0607
4.000 0.9397 0.01735 0.00761 -0.0561 0.4502 0.0754
4.250 0.9654 0.01743 0.00771 -0.0560 0.4476 0.1013
4.500 0.9912 0.01751 0.00783 -0.0560 0.4452 0.1337
4.750 1.0171 0.01757 0.00796 -0.0559 0.4430 0.2059
5.250 1.1847 0.01737 0.00915 -0.0810 0.4346 1.0000
5.500 1.2081 0.01759 0.00936 -0.0806 0.4321 1.0000
5.750 1.2314 0.01781 0.00954 -0.0801 0.4298 1.0000
6.000 1.2549 0.01803 0.00971 -0.0797 0.4277 1.0000
6.250 1.2770 0.01833 0.01006 -0.0792 0.4249 1.0000
6.500 1.2986 0.01865 0.01043 -0.0786 0.4218 1.0000
6.750 1.3202 0.01894 0.01076 -0.0779 0.4189 1.0000
7.000 1.3418 0.01922 0.01108 -0.0773 0.4164 1.0000
7.250 1.3635 0.01949 0.01134 -0.0766 0.4142 1.0000
7.500 1.3856 0.01976 0.01159 -0.0760 0.4122 1.0000
7.750 1.4050 0.02016 0.01209 -0.0751 0.4095 1.0000
8.000 1.4228 0.02055 0.01258 -0.0740 0.4055 1.0000
8.250 1.4404 0.02081 0.01286 -0.0728 0.4003 1.0000
8.500 1.4582 0.02104 0.01307 -0.0715 0.3950 1.0000
8.750 1.4709 0.02152 0.01369 -0.0697 0.3893 1.0000
9.000 1.4853 0.02190 0.01409 -0.0680 0.3847 1.0000
9.250 1.4979 0.02230 0.01450 -0.0661 0.3795 1.0000
9.500 1.5032 0.02295 0.01526 -0.0632 0.3730 1.0000
9.750 1.5065 0.02354 0.01585 -0.0600 0.3675 1.0000
10.000 1.5034 0.02443 0.01682 -0.0561 0.3627 1.0000
10.250 1.5010 0.02556 0.01804 -0.0530 0.3566 1.0000
10.500 1.5025 0.02670 0.01916 -0.0506 0.3501 1.0000
10.750 1.5010 0.02833 0.02091 -0.0486 0.3427 1.0000
11.000 1.5024 0.02985 0.02243 -0.0469 0.3357 1.0000
11.250 1.5008 0.03187 0.02457 -0.0454 0.3276 1.0000
11.500 1.4959 0.03421 0.02693 -0.0439 0.3170 1.0000
11.750 1.4889 0.03685 0.02957 -0.0425 0.3059 1.0000
12.000 1.4801 0.03985 0.03262 -0.0413 0.2934 1.0000
12.250 1.4685 0.04317 0.03595 -0.0401 0.2795 1.0000
12.500 1.4545 0.04687 0.03964 -0.0389 0.2644 1.0000
12.750 1.4389 0.05095 0.04369 -0.0380 0.2485 1.0000
13.000 1.4216 0.05540 0.04809 -0.0372 0.2298 1.0000
13.250 1.3995 0.06052 0.05314 -0.0365 0.2090 1.0000
13.500 1.3719 0.06650 0.05901 -0.0360 0.1856 1.0000
13.750 1.3450 0.07258 0.06499 -0.0357 0.1632 1.0000
14.000 1.3180 0.07887 0.07118 -0.0356 0.1396 1.0000
14.250 1.2914 0.08527 0.07748 -0.0357 0.1137 1.0000
14.500 1.2658 0.09172 0.08380 -0.0359 0.0847 1.0000
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