USA 22 AIRFOIL (usa22-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 22 AIRFOIL (usa22-il) Reynolds number: 50,000 Max Cl/Cd: 37.26 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa22-il-50000-n5.txt Download as CSV file: xf-usa22-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 22 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3535 0.10966 0.10320 -0.0175 1.0000 0.0993
-8.250 -0.3596 0.10803 0.10170 -0.0208 1.0000 0.1003
-8.000 -0.3593 0.10502 0.09882 -0.0227 1.0000 0.1008
-7.750 -0.3415 0.09964 0.09343 -0.0205 1.0000 0.1028
-7.500 -0.3357 0.09636 0.09021 -0.0207 1.0000 0.1042
-7.250 -0.3328 0.09328 0.08722 -0.0219 1.0000 0.1046
-7.000 -0.3299 0.08601 0.07994 -0.0300 1.0000 0.0566
-6.750 -0.3237 0.08252 0.07651 -0.0302 1.0000 0.0548
-6.500 -0.3186 0.07896 0.07303 -0.0318 1.0000 0.0539
-6.250 -0.3133 0.07537 0.06949 -0.0338 1.0000 0.0536
-6.000 -0.3071 0.07168 0.06585 -0.0359 1.0000 0.0538
-5.750 -0.2996 0.06789 0.06208 -0.0381 1.0000 0.0541
-5.500 -0.2909 0.06398 0.05815 -0.0402 1.0000 0.0543
-5.250 -0.2805 0.05993 0.05406 -0.0422 1.0000 0.0542
-5.000 -0.2682 0.05573 0.04975 -0.0443 1.0000 0.0538
-4.750 -0.2531 0.05119 0.04504 -0.0466 1.0000 0.0536
-4.500 -0.2349 0.04641 0.03996 -0.0492 1.0000 0.0540
-4.250 -0.1851 0.03902 0.03144 -0.0580 0.9906 0.0581
-4.000 -0.1443 0.03547 0.02768 -0.0625 0.9794 0.0623
-3.750 -0.0994 0.03181 0.02319 -0.0670 0.9680 0.0700
-3.500 -0.0569 0.02900 0.01984 -0.0705 0.9559 0.0775
-3.250 -0.0146 0.02702 0.01737 -0.0735 0.9431 0.0893
-3.000 0.0281 0.02532 0.01526 -0.0761 0.9303 0.0982
-2.750 0.0687 0.02407 0.01379 -0.0783 0.9164 0.1088
-2.500 0.1077 0.02318 0.01268 -0.0800 0.9012 0.1251
-2.250 0.1464 0.02227 0.01157 -0.0815 0.8853 0.1404
-2.000 0.1826 0.02152 0.01080 -0.0826 0.8683 0.1719
-1.750 0.2160 0.02100 0.01045 -0.0832 0.8501 0.2293
-1.500 0.2464 0.02078 0.01017 -0.0831 0.8298 0.2918
-1.250 0.2763 0.02046 0.00978 -0.0831 0.8108 0.3516
-1.000 0.3040 0.01988 0.00931 -0.0827 0.7918 0.4182
-0.750 0.3300 0.01914 0.00889 -0.0819 0.7727 0.4805
-0.500 0.3644 0.01775 0.00847 -0.0817 0.7544 1.0000
-0.250 0.3931 0.01791 0.00819 -0.0813 0.7367 1.0000
0.000 0.4205 0.01811 0.00800 -0.0807 0.7189 1.0000
0.250 0.4472 0.01835 0.00793 -0.0801 0.7014 1.0000
0.500 0.4737 0.01861 0.00791 -0.0795 0.6848 1.0000
0.750 0.5000 0.01888 0.00793 -0.0789 0.6688 1.0000
1.000 0.5261 0.01918 0.00800 -0.0784 0.6537 1.0000
1.250 0.5522 0.01948 0.00811 -0.0778 0.6392 1.0000
1.500 0.5786 0.01980 0.00826 -0.0774 0.6253 1.0000
1.750 0.6049 0.02013 0.00844 -0.0769 0.6121 1.0000
2.000 0.6312 0.02046 0.00863 -0.0765 0.5993 1.0000
2.250 0.6576 0.02079 0.00883 -0.0760 0.5873 1.0000
2.500 0.6833 0.02116 0.00912 -0.0755 0.5744 1.0000
2.750 0.7089 0.02154 0.00943 -0.0750 0.5618 1.0000
3.000 0.7343 0.02192 0.00978 -0.0745 0.5495 1.0000
3.250 0.7597 0.02230 0.01011 -0.0740 0.5376 1.0000
3.500 0.7852 0.02268 0.01042 -0.0734 0.5261 1.0000
3.750 0.8107 0.02305 0.01078 -0.0729 0.5148 1.0000
4.000 0.8353 0.02351 0.01125 -0.0723 0.5025 1.0000
4.250 0.8599 0.02396 0.01174 -0.0718 0.4907 1.0000
4.500 0.8847 0.02442 0.01224 -0.0712 0.4795 1.0000
4.750 0.9098 0.02485 0.01267 -0.0706 0.4689 1.0000
5.000 0.9340 0.02537 0.01325 -0.0700 0.4574 1.0000
5.250 0.9578 0.02593 0.01392 -0.0694 0.4458 1.0000
5.500 0.9818 0.02650 0.01461 -0.0688 0.4351 1.0000
5.750 1.0065 0.02701 0.01516 -0.0682 0.4252 1.0000
6.000 1.0295 0.02767 0.01598 -0.0675 0.4138 1.0000
6.250 1.0523 0.02839 0.01687 -0.0668 0.4030 1.0000
6.500 1.0757 0.02904 0.01769 -0.0662 0.3930 1.0000
6.750 1.0989 0.02970 0.01849 -0.0655 0.3831 1.0000
7.000 1.1202 0.03060 0.01964 -0.0647 0.3727 1.0000
7.250 1.1430 0.03138 0.02059 -0.0640 0.3641 1.0000
7.500 1.1649 0.03222 0.02167 -0.0632 0.3549 1.0000
7.750 1.1843 0.03292 0.02266 -0.0621 0.3427 1.0000
8.000 1.2016 0.03268 0.02245 -0.0603 0.3226 1.0000
8.250 1.2137 0.03290 0.02283 -0.0582 0.2988 1.0000
8.500 1.2290 0.03340 0.02348 -0.0566 0.2821 1.0000
8.750 1.2417 0.03410 0.02434 -0.0548 0.2628 1.0000
9.000 1.2517 0.03497 0.02531 -0.0529 0.2402 1.0000
9.250 1.2582 0.03619 0.02658 -0.0509 0.2137 1.0000
9.500 1.2629 0.03775 0.02819 -0.0489 0.1869 1.0000
9.750 1.2621 0.03973 0.03016 -0.0467 0.1544 1.0000
10.000 1.2543 0.04253 0.03277 -0.0447 0.0952 1.0000
10.250 1.2325 0.04718 0.03696 -0.0438 0.0620 1.0000
10.500 1.2165 0.05194 0.04173 -0.0440 0.0503 1.0000
10.750 1.2045 0.05667 0.04653 -0.0447 0.0463 1.0000
11.000 1.1925 0.06169 0.05168 -0.0458 0.0437 1.0000
11.250 1.1811 0.06683 0.05696 -0.0472 0.0420 1.0000
11.500 1.1699 0.07211 0.06241 -0.0488 0.0405 1.0000
11.750 1.1584 0.07752 0.06799 -0.0504 0.0394 1.0000
12.000 1.1467 0.08302 0.07366 -0.0521 0.0384 1.0000
12.250 1.1352 0.08857 0.07934 -0.0538 0.0375 1.0000
12.500 1.1240 0.09409 0.08499 -0.0556 0.0367 1.0000
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Polar data table (+)
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