USA 27 mod. AIRFOIL (usa27m2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 27 mod. AIRFOIL (usa27m2-il) Reynolds number: 500,000 Max Cl/Cd: 86.84 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa27m2-il-500000.txt Download as CSV file: xf-usa27m2-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: USA 27 mod. AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2048 0.08947 0.08714 -0.0698 0.9838 0.0306
-9.000 -0.1944 0.08564 0.08332 -0.0733 0.9797 0.0313
-8.750 -0.1835 0.08093 0.07861 -0.0785 0.9758 0.0324
-8.500 -0.2078 0.06610 0.06374 -0.0981 0.9642 0.0342
-8.250 -0.1863 0.06354 0.06116 -0.1006 0.9617 0.0346
-8.000 -0.1611 0.06047 0.05805 -0.1049 0.9598 0.0350
-7.750 -0.1442 0.05734 0.05489 -0.1077 0.9551 0.0355
-7.500 -0.1312 0.05385 0.05134 -0.1101 0.9485 0.0362
-7.250 -0.1134 0.04876 0.04613 -0.1145 0.9446 0.0375
-7.000 -0.1369 0.03593 0.03253 -0.1161 0.9321 0.0409
-6.750 -0.1108 0.03414 0.03073 -0.1171 0.9290 0.0415
-6.500 -0.0975 0.03279 0.02932 -0.1153 0.9206 0.0422
-6.250 -0.0762 0.03072 0.02707 -0.1153 0.9153 0.0438
-6.000 -0.0716 0.02775 0.02351 -0.1121 0.9058 0.0480
-5.750 -0.0458 0.02634 0.02213 -0.1124 0.9002 0.0491
-5.500 -0.0245 0.02528 0.02101 -0.1116 0.8930 0.0509
-5.250 -0.0086 0.02376 0.01901 -0.1096 0.8852 0.0564
-5.000 0.0157 0.02247 0.01778 -0.1093 0.8780 0.0578
-4.750 0.0389 0.02168 0.01689 -0.1086 0.8697 0.0608
-4.500 0.0588 0.02048 0.01544 -0.1072 0.8613 0.0670
-4.250 0.0836 0.01960 0.01455 -0.1068 0.8527 0.0698
-4.000 0.1036 0.01880 0.01350 -0.1053 0.8430 0.0782
-3.750 0.1337 0.01514 0.00901 -0.1030 0.8345 0.0444
-3.500 0.1586 0.01428 0.00783 -0.1016 0.8230 0.0405
-3.250 0.1847 0.01420 0.00765 -0.1009 0.8107 0.0400
-3.000 0.2107 0.01306 0.00646 -0.1003 0.7978 0.0392
-2.750 0.2356 0.01249 0.00582 -0.0995 0.7830 0.0390
-2.500 0.2594 0.01206 0.00531 -0.0984 0.7657 0.0390
-2.250 0.2825 0.01171 0.00488 -0.0972 0.7450 0.0391
-2.000 0.3046 0.01145 0.00451 -0.0958 0.7210 0.0392
-1.750 0.3260 0.01127 0.00420 -0.0942 0.6958 0.0394
-1.500 0.3468 0.01115 0.00395 -0.0926 0.6729 0.0396
-1.250 0.3681 0.01110 0.00377 -0.0911 0.6538 0.0400
-0.750 0.4111 0.01079 0.00329 -0.0882 0.6229 0.0417
-0.500 0.4339 0.01071 0.00316 -0.0871 0.6094 0.0424
-0.250 0.4567 0.01068 0.00306 -0.0859 0.5960 0.0435
0.000 0.4793 0.01067 0.00298 -0.0847 0.5816 0.0448
0.250 0.5016 0.01069 0.00292 -0.0835 0.5651 0.0463
0.500 0.5233 0.01071 0.00286 -0.0821 0.5461 0.0494
0.750 0.5440 0.01070 0.00284 -0.0805 0.5245 0.0633
1.000 0.5601 0.01040 0.00290 -0.0783 0.5029 0.2159
1.250 0.5797 0.01045 0.00301 -0.0767 0.4808 0.2721
1.500 0.5999 0.01058 0.00311 -0.0751 0.4609 0.3076
1.750 0.6207 0.01070 0.00322 -0.0738 0.4447 0.3420
2.000 0.6419 0.01079 0.00332 -0.0725 0.4320 0.3754
2.250 0.6601 0.01054 0.00337 -0.0708 0.4223 0.4958
2.500 0.7335 0.01022 0.00419 -0.0803 0.4104 0.9743
2.750 0.8098 0.01074 0.00456 -0.0910 0.4000 0.9896
3.000 0.8822 0.01102 0.00473 -0.1009 0.3910 0.9980
3.250 0.9169 0.01123 0.00485 -0.1027 0.3847 1.0000
3.500 0.9370 0.01134 0.00495 -0.1011 0.3795 1.0000
3.750 0.9558 0.01149 0.00507 -0.0994 0.3745 1.0000
4.000 0.9734 0.01171 0.00522 -0.0974 0.3698 1.0000
4.250 0.9930 0.01181 0.00533 -0.0958 0.3660 1.0000
4.500 1.0119 0.01194 0.00546 -0.0941 0.3618 1.0000
4.750 1.0295 0.01211 0.00559 -0.0921 0.3575 1.0000
5.000 1.0457 0.01234 0.00577 -0.0898 0.3529 1.0000
5.250 1.0642 0.01243 0.00590 -0.0880 0.3494 1.0000
5.500 1.0818 0.01256 0.00604 -0.0860 0.3457 1.0000
5.750 1.0980 0.01272 0.00619 -0.0837 0.3421 1.0000
6.000 1.1116 0.01291 0.00636 -0.0809 0.3386 1.0000
6.250 1.1256 0.01309 0.00653 -0.0782 0.3353 1.0000
6.500 1.1407 0.01319 0.00667 -0.0757 0.3321 1.0000
6.750 1.1553 0.01331 0.00682 -0.0732 0.3276 1.0000
7.000 1.1686 0.01352 0.00699 -0.0704 0.3226 1.0000
7.250 1.1841 0.01370 0.00718 -0.0681 0.3178 1.0000
7.500 1.2010 0.01383 0.00735 -0.0661 0.3126 1.0000
7.750 1.2157 0.01406 0.00756 -0.0637 0.3068 1.0000
8.000 1.2323 0.01427 0.00779 -0.0617 0.3014 1.0000
8.250 1.2499 0.01446 0.00800 -0.0600 0.2952 1.0000
8.500 1.2649 0.01477 0.00828 -0.0578 0.2891 1.0000
8.750 1.2838 0.01497 0.00854 -0.0564 0.2824 1.0000
9.000 1.2990 0.01532 0.00885 -0.0544 0.2733 1.0000
9.250 1.3164 0.01561 0.00915 -0.0528 0.2614 1.0000
9.500 1.3317 0.01603 0.00953 -0.0510 0.2469 1.0000
9.750 1.3448 0.01659 0.01001 -0.0489 0.2293 1.0000
10.000 1.3563 0.01727 0.01059 -0.0467 0.2094 1.0000
10.250 1.3662 0.01808 0.01129 -0.0443 0.1926 1.0000
10.500 1.3758 0.01894 0.01208 -0.0419 0.1792 1.0000
10.750 1.3852 0.01983 0.01292 -0.0397 0.1680 1.0000
11.250 1.4048 0.02168 0.01470 -0.0355 0.1464 1.0000
11.500 1.4128 0.02275 0.01570 -0.0334 0.1312 1.0000
11.750 1.4135 0.02434 0.01710 -0.0306 0.1010 1.0000
12.000 1.3941 0.02737 0.01985 -0.0261 0.0607 1.0000
12.250 1.3743 0.03069 0.02302 -0.0221 0.0278 1.0000
12.500 1.3751 0.03264 0.02503 -0.0203 0.0237 1.0000
12.750 1.3778 0.03453 0.02700 -0.0187 0.0221 1.0000
13.000 1.3793 0.03662 0.02918 -0.0174 0.0209 1.0000
13.250 1.3827 0.03864 0.03130 -0.0163 0.0202 1.0000
13.500 1.3847 0.04089 0.03366 -0.0154 0.0195 1.0000
13.750 1.3851 0.04341 0.03629 -0.0146 0.0190 1.0000
14.000 1.3834 0.04628 0.03927 -0.0141 0.0186 1.0000
14.250 1.3794 0.04950 0.04260 -0.0137 0.0182 1.0000
14.500 1.3726 0.05318 0.04639 -0.0135 0.0179 1.0000
14.750 1.3631 0.05729 0.05063 -0.0135 0.0176 1.0000
15.000 1.3513 0.06180 0.05527 -0.0137 0.0173 1.0000
15.250 1.3390 0.06652 0.06013 -0.0142 0.0172 1.0000
15.500 1.3309 0.07079 0.06451 -0.0147 0.0170 1.0000
15.750 1.3215 0.07535 0.06919 -0.0154 0.0169 1.0000
16.000 1.3110 0.08011 0.07407 -0.0163 0.0168 1.0000
16.250 1.3002 0.08503 0.07910 -0.0173 0.0166 1.0000
16.500 1.2889 0.09006 0.08424 -0.0185 0.0165 1.0000
16.750 1.2778 0.09509 0.08938 -0.0196 0.0164 1.0000
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