USA 27 AIRFOIL (usa27-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: USA 27 AIRFOIL (usa27-il) Reynolds number: 100,000 Max Cl/Cd: 52.81 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa27-il-100000-n5.txt Download as CSV file: xf-usa27-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3236 0.10794 0.10333 -0.0314 1.0000 0.0613
-8.500 -0.3459 0.10714 0.10265 -0.0309 1.0000 0.0622
-8.250 -0.3658 0.10589 0.10151 -0.0314 0.9986 0.0625
-8.000 -0.3570 0.10083 0.09646 -0.0361 0.9936 0.0634
-7.750 -0.3334 0.09688 0.09249 -0.0332 0.9931 0.0653
-7.500 -0.3196 0.09342 0.08903 -0.0357 0.9880 0.0674
-7.250 -0.3064 0.08959 0.08519 -0.0405 0.9815 0.0702
-7.000 -0.2918 0.08455 0.07997 -0.0578 0.9674 0.0750
-6.750 -0.2774 0.07967 0.07516 -0.0570 0.9643 0.0764
-6.500 -0.2582 0.07684 0.07233 -0.0561 0.9610 0.0794
-6.250 -0.2425 0.07359 0.06904 -0.0587 0.9530 0.0835
-6.000 -0.2236 0.06839 0.06358 -0.0683 0.9422 0.0896
-5.500 -0.1816 0.06175 0.05691 -0.0703 0.9320 0.0932
-5.000 -0.1371 0.04455 0.03851 -0.0787 0.9142 0.0530
-4.750 -0.1116 0.04150 0.03523 -0.0797 0.9075 0.0511
-4.500 -0.0832 0.03816 0.03159 -0.0811 0.9012 0.0500
-4.250 -0.0573 0.03506 0.02808 -0.0815 0.8920 0.0491
-4.000 -0.0287 0.03235 0.02490 -0.0819 0.8833 0.0492
-3.750 0.0042 0.03005 0.02212 -0.0829 0.8757 0.0501
-3.500 0.0314 0.02824 0.01995 -0.0826 0.8658 0.0500
-3.250 0.0662 0.02643 0.01777 -0.0837 0.8593 0.0497
-3.000 0.0927 0.02513 0.01618 -0.0831 0.8485 0.0495
-2.750 0.1274 0.02378 0.01455 -0.0840 0.8411 0.0495
-2.500 0.1560 0.02275 0.01331 -0.0837 0.8300 0.0496
-2.250 0.1850 0.02184 0.01224 -0.0836 0.8187 0.0499
-2.000 0.2176 0.02103 0.01126 -0.0841 0.8084 0.0511
-1.750 0.2489 0.02031 0.01042 -0.0844 0.7968 0.0525
-1.500 0.2765 0.01956 0.00966 -0.0841 0.7831 0.0535
-1.250 0.3049 0.01895 0.00902 -0.0839 0.7689 0.0542
-1.000 0.3334 0.01844 0.00844 -0.0837 0.7541 0.0550
-0.750 0.3621 0.01801 0.00793 -0.0836 0.7387 0.0561
-0.500 0.3912 0.01765 0.00746 -0.0835 0.7226 0.0576
-0.250 0.4208 0.01735 0.00704 -0.0835 0.7063 0.0595
0.000 0.4508 0.01713 0.00666 -0.0835 0.6901 0.0621
0.250 0.4808 0.01688 0.00633 -0.0836 0.6741 0.0690
0.500 0.5104 0.01668 0.00606 -0.0837 0.6583 0.0841
0.750 0.5372 0.01626 0.00610 -0.0836 0.6430 0.2506
1.000 0.5627 0.01613 0.00610 -0.0831 0.6281 0.3450
1.250 0.5823 0.01539 0.00605 -0.0815 0.6145 0.5652
1.750 0.7124 0.01543 0.00633 -0.0965 0.5793 1.0000
2.250 0.7560 0.01587 0.00652 -0.0941 0.5514 1.0000
2.500 0.7777 0.01610 0.00663 -0.0928 0.5386 1.0000
2.750 0.7995 0.01634 0.00674 -0.0916 0.5266 1.0000
3.000 0.8208 0.01659 0.00689 -0.0903 0.5142 1.0000
3.250 0.8417 0.01684 0.00705 -0.0890 0.5017 1.0000
3.500 0.8627 0.01710 0.00722 -0.0876 0.4901 1.0000
3.750 0.8837 0.01737 0.00739 -0.0863 0.4796 1.0000
4.000 0.9045 0.01766 0.00760 -0.0850 0.4690 1.0000
4.250 0.9254 0.01795 0.00784 -0.0837 0.4592 1.0000
4.500 0.9464 0.01827 0.00806 -0.0824 0.4503 1.0000
4.750 0.9670 0.01858 0.00836 -0.0811 0.4407 1.0000
5.000 0.9881 0.01892 0.00863 -0.0799 0.4326 1.0000
5.250 1.0088 0.01925 0.00896 -0.0787 0.4241 1.0000
5.500 1.0298 0.01961 0.00929 -0.0775 0.4164 1.0000
5.750 1.0503 0.01996 0.00965 -0.0762 0.4084 1.0000
6.000 1.0716 0.02034 0.01000 -0.0751 0.4017 1.0000
6.250 1.0923 0.02070 0.01045 -0.0740 0.3946 1.0000
6.500 1.1137 0.02109 0.01082 -0.0729 0.3885 1.0000
6.750 1.1337 0.02148 0.01130 -0.0717 0.3815 1.0000
7.000 1.1539 0.02187 0.01173 -0.0704 0.3746 1.0000
7.250 1.1739 0.02229 0.01222 -0.0692 0.3679 1.0000
7.500 1.1931 0.02270 0.01272 -0.0678 0.3607 1.0000
7.750 1.2133 0.02313 0.01317 -0.0666 0.3546 1.0000
8.000 1.2299 0.02355 0.01373 -0.0648 0.3458 1.0000
8.250 1.2440 0.02395 0.01419 -0.0626 0.3347 1.0000
8.500 1.2559 0.02435 0.01461 -0.0600 0.3222 1.0000
8.750 1.2671 0.02479 0.01512 -0.0574 0.3099 1.0000
9.000 1.2781 0.02527 0.01570 -0.0547 0.2982 1.0000
9.250 1.2865 0.02580 0.01629 -0.0517 0.2839 1.0000
9.500 1.2938 0.02642 0.01697 -0.0488 0.2673 1.0000
9.750 1.3030 0.02712 0.01772 -0.0462 0.2525 1.0000
10.000 1.3115 0.02792 0.01855 -0.0437 0.2372 1.0000
10.250 1.3176 0.02888 0.01951 -0.0411 0.2199 1.0000
10.500 1.3192 0.03018 0.02070 -0.0382 0.1980 1.0000
10.750 1.3192 0.03171 0.02214 -0.0354 0.1813 1.0000
11.000 1.3218 0.03324 0.02369 -0.0330 0.1693 1.0000
11.250 1.3238 0.03489 0.02538 -0.0308 0.1582 1.0000
11.500 1.3229 0.03688 0.02738 -0.0287 0.1419 1.0000
11.750 1.3225 0.03895 0.02948 -0.0269 0.1225 1.0000
12.250 1.2844 0.04696 0.03702 -0.0230 0.0443 1.0000
12.500 1.2657 0.05149 0.04148 -0.0221 0.0348 1.0000
12.750 1.2537 0.05563 0.04569 -0.0217 0.0313 1.0000
13.000 1.2444 0.05969 0.04989 -0.0217 0.0294 1.0000
13.250 1.2360 0.06380 0.05417 -0.0219 0.0282 1.0000
13.500 1.2272 0.06815 0.05868 -0.0224 0.0274 1.0000
13.750 1.2173 0.07278 0.06349 -0.0232 0.0268 1.0000
14.000 1.2064 0.07770 0.06860 -0.0241 0.0263 1.0000
14.250 1.1951 0.08285 0.07391 -0.0253 0.0258 1.0000
14.500 1.1835 0.08816 0.07939 -0.0267 0.0255 1.0000
14.750 1.1716 0.09364 0.08503 -0.0282 0.0251 1.0000
15.000 1.1594 0.09927 0.09083 -0.0299 0.0248 1.0000
15.250 1.1472 0.10502 0.09674 -0.0318 0.0245 1.0000
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Polar data table (+)
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