USA 31 AIRFOIL (usa31-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: USA 31 AIRFOIL (usa31-il) Reynolds number: 500,000 Max Cl/Cd: 76.83 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa31-il-500000.txt Download as CSV file: xf-usa31-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: USA 31 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
------ -------- --------- --------- -------- -------- --------
-10.750 0.2821 0.09154 0.08871 -0.1686 0.9448 0.0293
-10.500 0.3040 0.08878 0.08594 -0.1722 0.9441 0.0296
-10.250 0.2990 0.08779 0.08498 -0.1686 0.9362 0.0300
-10.000 0.3155 0.08509 0.08227 -0.1713 0.9339 0.0306
-9.750 0.3327 0.08216 0.07933 -0.1747 0.9319 0.0317
-9.250 0.3256 0.07536 0.07253 -0.1792 0.9196 0.0332
-9.000 0.3450 0.07316 0.07032 -0.1800 0.9173 0.0335
-8.750 0.3664 0.07097 0.06811 -0.1820 0.9152 0.0338
-8.500 0.3682 0.06966 0.06682 -0.1798 0.9084 0.0341
-8.250 0.3774 0.06774 0.06490 -0.1800 0.9032 0.0344
-8.000 0.3936 0.06533 0.06247 -0.1822 0.8997 0.0350
-7.750 0.3891 0.06389 0.06105 -0.1796 0.8907 0.0357
-7.500 0.3956 0.06114 0.05827 -0.1814 0.8848 0.0370
-7.250 0.3533 0.05607 0.05318 -0.1822 0.8701 0.0382
-7.000 0.3632 0.05486 0.05197 -0.1802 0.8631 0.0385
-6.750 0.3761 0.05353 0.05061 -0.1797 0.8560 0.0388
-6.500 0.3884 0.05192 0.04897 -0.1800 0.8490 0.0391
-6.250 0.3976 0.05042 0.04744 -0.1796 0.8407 0.0397
-6.000 0.4097 0.04839 0.04536 -0.1807 0.8333 0.0407
-5.500 0.4046 0.02632 0.02327 -0.1717 0.7935 0.0448
-5.250 0.3940 0.01446 0.01072 -0.1850 0.7876 0.0506
-5.000 0.4193 0.02664 0.02273 -0.1921 0.7956 0.0511
-4.750 0.4404 0.02581 0.02189 -0.1913 0.7882 0.0519
-4.500 0.4553 0.02487 0.02089 -0.1896 0.7798 0.0532
-4.250 0.4648 0.02235 0.01783 -0.1880 0.7709 0.0586
-4.000 0.4798 0.02158 0.01709 -0.1858 0.7618 0.0597
-3.750 0.4957 0.02102 0.01604 -0.1839 0.7527 0.0662
-3.500 0.5084 0.01975 0.01489 -0.1813 0.7430 0.0677
-3.000 0.5367 0.01846 0.01334 -0.1763 0.7233 0.0772
-2.750 0.5526 0.01800 0.01289 -0.1739 0.7136 0.0802
-2.500 0.5596 0.01489 0.00851 -0.1670 0.7043 0.0441
-2.250 0.5769 0.01416 0.00774 -0.1647 0.6955 0.0427
-2.000 0.5930 0.01360 0.00708 -0.1621 0.6862 0.0417
-1.750 0.6109 0.01321 0.00657 -0.1598 0.6776 0.0412
-1.500 0.6289 0.01293 0.00618 -0.1576 0.6688 0.0408
-1.250 0.6487 0.01270 0.00587 -0.1558 0.6613 0.0407
-1.000 0.6673 0.01252 0.00563 -0.1537 0.6534 0.0406
-0.750 0.6889 0.01240 0.00542 -0.1523 0.6463 0.0408
-0.500 0.7065 0.01230 0.00531 -0.1501 0.6388 0.0412
-0.250 0.7273 0.01227 0.00520 -0.1486 0.6314 0.0421
0.000 0.7472 0.01222 0.00513 -0.1469 0.6248 0.0424
0.250 0.7666 0.01219 0.00507 -0.1451 0.6179 0.0425
0.500 0.7895 0.01220 0.00499 -0.1440 0.6111 0.0430
0.750 0.8069 0.01221 0.00500 -0.1418 0.6045 0.0436
1.000 0.8268 0.01221 0.00496 -0.1401 0.5974 0.0440
1.250 0.8484 0.01221 0.00489 -0.1388 0.5911 0.0454
1.500 0.8671 0.01223 0.00491 -0.1370 0.5843 0.0470
1.750 0.8870 0.01232 0.00493 -0.1354 0.5773 0.0487
2.000 0.9064 0.01239 0.00498 -0.1337 0.5707 0.0524
2.250 0.9248 0.01229 0.00506 -0.1319 0.5634 0.1180
2.500 0.9442 0.01229 0.00533 -0.1304 0.5566 0.2533
2.750 0.9620 0.01253 0.00562 -0.1284 0.5493 0.2750
3.000 0.9796 0.01286 0.00590 -0.1264 0.5417 0.2869
3.250 0.9977 0.01316 0.00619 -0.1246 0.5346 0.2948
3.500 1.0152 0.01347 0.00648 -0.1226 0.5270 0.3011
3.750 1.0328 0.01381 0.00673 -0.1208 0.5200 0.3077
4.000 1.0495 0.01408 0.00704 -0.1187 0.5122 0.3127
4.250 1.0657 0.01443 0.00734 -0.1167 0.5050 0.3176
4.500 1.0836 0.01472 0.00761 -0.1149 0.4981 0.3226
4.750 1.1002 0.01504 0.00793 -0.1130 0.4908 0.3290
5.000 1.1176 0.01533 0.00818 -0.1112 0.4841 0.3316
5.250 1.1357 0.01555 0.00841 -0.1097 0.4774 0.3332
5.500 1.1526 0.01584 0.00864 -0.1079 0.4706 0.3346
5.750 1.1715 0.01609 0.00888 -0.1065 0.4647 0.3363
6.000 1.1892 0.01637 0.00914 -0.1050 0.4580 0.3385
6.250 1.2054 0.01675 0.00944 -0.1032 0.4515 0.3400
6.500 1.2228 0.01701 0.00973 -0.1016 0.4448 0.3413
6.750 1.2395 0.01732 0.01003 -0.1000 0.4381 0.3427
7.000 1.2564 0.01768 0.01037 -0.0985 0.4320 0.3441
7.250 1.2746 0.01798 0.01071 -0.0972 0.4267 0.3456
7.500 1.2916 0.01835 0.01108 -0.0957 0.4214 0.3473
7.750 1.3083 0.01878 0.01146 -0.0942 0.4159 0.3490
8.000 1.3263 0.01910 0.01185 -0.0930 0.4110 0.3507
8.250 1.3410 0.01957 0.01231 -0.0912 0.4044 0.3527
8.500 1.3563 0.02007 0.01276 -0.0896 0.3990 0.3543
8.750 1.3738 0.02047 0.01322 -0.0884 0.3944 0.3558
9.000 1.3899 0.02091 0.01370 -0.0870 0.3887 0.3579
9.250 1.4049 0.02144 0.01423 -0.0855 0.3838 0.3603
9.500 1.4204 0.02196 0.01478 -0.0841 0.3785 0.3624
9.750 1.4367 0.02245 0.01534 -0.0828 0.3734 0.3643
10.000 1.4503 0.02309 0.01597 -0.0813 0.3680 0.3664
10.250 1.4642 0.02374 0.01661 -0.0798 0.3629 0.3684
10.500 1.4798 0.02430 0.01725 -0.0785 0.3578 0.3705
10.750 1.4936 0.02498 0.01796 -0.0772 0.3525 0.3725
11.000 1.5061 0.02576 0.01873 -0.0756 0.3475 0.3746
11.250 1.5209 0.02643 0.01949 -0.0745 0.3419 0.3769
11.500 1.5324 0.02729 0.02038 -0.0730 0.3354 0.3790
11.750 1.5426 0.02826 0.02134 -0.0713 0.3294 0.3818
12.000 1.5547 0.02915 0.02230 -0.0700 0.3224 0.3841
12.250 1.5625 0.03033 0.02346 -0.0683 0.3150 0.3861
12.500 1.5739 0.03135 0.02455 -0.0671 0.3077 0.3894
12.750 1.5820 0.03260 0.02581 -0.0656 0.3002 0.3920
13.000 1.5910 0.03382 0.02707 -0.0643 0.2934 0.3952
13.250 1.5991 0.03514 0.02842 -0.0629 0.2858 0.3982
13.500 1.6049 0.03665 0.02995 -0.0614 0.2783 0.4004
13.750 1.6137 0.03803 0.03138 -0.0604 0.2708 0.4036
14.000 1.6175 0.03981 0.03316 -0.0589 0.2632 0.4065
14.250 1.6234 0.04148 0.03487 -0.0578 0.2547 0.4098
14.500 1.6268 0.04339 0.03679 -0.0565 0.2477 0.4134
14.750 1.6322 0.04521 0.03867 -0.0556 0.2399 0.4169
15.000 1.6333 0.04743 0.04090 -0.0544 0.2322 0.4207
15.250 1.6370 0.04947 0.04298 -0.0535 0.2244 0.4259
15.500 1.6366 0.05193 0.04546 -0.0525 0.2178 0.4319
15.750 1.6410 0.05403 0.04762 -0.0519 0.2104 0.4425
16.000 1.7349 0.06188 0.05625 -0.0765 0.1882 1.0000
16.250 1.7352 0.06440 0.05882 -0.0756 0.1820 1.0000
16.500 1.7290 0.06766 0.06209 -0.0746 0.1759 1.0000
16.750 1.7281 0.07038 0.06484 -0.0738 0.1697 1.0000
17.000 1.7210 0.07383 0.06831 -0.0730 0.1631 1.0000
17.250 1.7167 0.07699 0.07152 -0.0723 0.1576 1.0000
17.500 1.7108 0.08039 0.07494 -0.0717 0.1506 1.0000
17.750 1.7031 0.08406 0.07865 -0.0712 0.1451 1.0000
18.000 1.6968 0.08763 0.08224 -0.0708 0.1378 1.0000
18.250 1.6870 0.09163 0.08627 -0.0705 0.1314 1.0000
18.500 1.6783 0.09556 0.09022 -0.0704 0.1235 1.0000
18.750 1.6686 0.09969 0.09438 -0.0704 0.1171 1.0000
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Polar data table (+)
Polar graphs
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