USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 40 B AIRFOIL (usa40b-il) Reynolds number: 50,000 Max Cl/Cd: 31.18 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa40b-il-50000-n5.txt Download as CSV file: xf-usa40b-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 40 B 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2841 0.09951 0.09218 -0.0338 1.0000 0.0869
-8.500 -0.2869 0.09637 0.08914 -0.0341 1.0000 0.0856
-8.250 -0.2926 0.09321 0.08607 -0.0344 1.0000 0.0846
-7.750 -0.3442 0.08440 0.07756 -0.0371 1.0000 0.0803
-7.500 -0.3536 0.08135 0.07462 -0.0370 1.0000 0.0801
-7.250 -0.3639 0.07790 0.07126 -0.0376 1.0000 0.0798
-7.000 -0.3745 0.07417 0.06760 -0.0386 1.0000 0.0794
-6.750 -0.3853 0.07035 0.06382 -0.0395 1.0000 0.0790
-6.500 -0.3945 0.06649 0.05993 -0.0405 1.0000 0.0786
-6.250 -0.4009 0.06242 0.05578 -0.0419 1.0000 0.0782
-6.000 -0.3780 0.05578 0.04877 -0.0502 0.9911 0.0777
-5.750 -0.3468 0.04965 0.04210 -0.0582 0.9808 0.0776
-5.500 -0.3121 0.04473 0.03658 -0.0645 0.9706 0.0783
-5.250 -0.2760 0.04067 0.03175 -0.0695 0.9594 0.0803
-5.000 -0.2391 0.03867 0.02968 -0.0724 0.9473 0.0825
-4.750 -0.1999 0.03657 0.02732 -0.0755 0.9345 0.0847
-4.500 -0.1578 0.03433 0.02470 -0.0787 0.9223 0.0869
-4.250 -0.1152 0.03231 0.02223 -0.0815 0.9096 0.0901
-4.000 -0.0787 0.03093 0.02080 -0.0831 0.8952 0.0941
-3.750 -0.0403 0.02966 0.01939 -0.0847 0.8816 0.0994
-3.500 0.0026 0.02825 0.01784 -0.0867 0.8702 0.1048
-3.250 0.0364 0.02729 0.01686 -0.0873 0.8547 0.1125
-3.000 0.0690 0.02636 0.01596 -0.0876 0.8385 0.1218
-2.750 0.1025 0.02550 0.01512 -0.0881 0.8219 0.1352
-2.500 0.1359 0.02473 0.01437 -0.0884 0.8044 0.1548
-2.250 0.1697 0.02395 0.01367 -0.0889 0.7862 0.1854
-2.000 0.2030 0.02307 0.01293 -0.0893 0.7672 0.2345
-1.750 0.2350 0.02225 0.01237 -0.0895 0.7472 0.3011
-1.500 0.2656 0.02164 0.01198 -0.0893 0.7262 0.3804
-1.250 0.2931 0.02119 0.01175 -0.0882 0.7041 0.4642
-1.000 0.3133 0.02095 0.01190 -0.0854 0.6801 0.5653
-0.750 0.3315 0.02092 0.01203 -0.0820 0.6559 0.6612
-0.500 0.3505 0.02090 0.01195 -0.0788 0.6318 0.7305
-0.250 0.3706 0.02082 0.01174 -0.0761 0.6075 0.7808
0.000 0.3911 0.02069 0.01149 -0.0737 0.5822 0.8269
0.250 0.4178 0.02051 0.01114 -0.0724 0.5578 0.8777
0.500 0.4650 0.02043 0.01080 -0.0755 0.5305 1.0000
0.750 0.4918 0.02074 0.01075 -0.0755 0.5095 1.0000
1.000 0.5188 0.02110 0.01077 -0.0754 0.4907 1.0000
1.250 0.5460 0.02150 0.01085 -0.0754 0.4741 1.0000
1.500 0.5734 0.02193 0.01096 -0.0754 0.4595 1.0000
1.750 0.6008 0.02238 0.01115 -0.0753 0.4458 1.0000
2.000 0.6278 0.02287 0.01144 -0.0753 0.4330 1.0000
2.250 0.6555 0.02336 0.01170 -0.0753 0.4223 1.0000
2.500 0.6827 0.02389 0.01206 -0.0752 0.4118 1.0000
2.750 0.7099 0.02443 0.01243 -0.0752 0.4026 1.0000
3.000 0.7367 0.02499 0.01285 -0.0750 0.3935 1.0000
3.250 0.7640 0.02557 0.01325 -0.0750 0.3859 1.0000
3.500 0.7898 0.02619 0.01383 -0.0748 0.3778 1.0000
3.750 0.8174 0.02680 0.01426 -0.0747 0.3715 1.0000
4.000 0.8429 0.02749 0.01493 -0.0745 0.3649 1.0000
4.250 0.8681 0.02818 0.01558 -0.0741 0.3584 1.0000
4.500 0.8952 0.02882 0.01607 -0.0740 0.3530 1.0000
4.750 0.9196 0.02961 0.01687 -0.0737 0.3474 1.0000
5.000 0.9433 0.03043 0.01773 -0.0732 0.3419 1.0000
5.250 0.9686 0.03121 0.01846 -0.0729 0.3374 1.0000
5.500 0.9958 0.03194 0.01909 -0.0729 0.3336 1.0000
5.750 1.0168 0.03297 0.02023 -0.0722 0.3290 1.0000
6.000 1.0379 0.03399 0.02135 -0.0715 0.3243 1.0000
6.250 1.0609 0.03490 0.02228 -0.0710 0.3201 1.0000
6.500 1.0860 0.03573 0.02305 -0.0707 0.3167 1.0000
6.750 1.1091 0.03677 0.02410 -0.0703 0.3136 1.0000
7.000 1.1241 0.03825 0.02582 -0.0691 0.3099 1.0000
7.250 1.1406 0.03968 0.02741 -0.0681 0.3065 1.0000
7.500 1.1589 0.04096 0.02878 -0.0673 0.3032 1.0000
7.750 1.1799 0.04207 0.02992 -0.0667 0.3003 1.0000
8.000 1.2042 0.04304 0.03087 -0.0663 0.2977 1.0000
8.250 1.2139 0.04489 0.03292 -0.0648 0.2947 1.0000
8.500 1.2143 0.04729 0.03561 -0.0627 0.2914 1.0000
8.750 1.2158 0.04970 0.03824 -0.0607 0.2886 1.0000
9.000 1.2170 0.05212 0.04083 -0.0589 0.2860 1.0000
9.250 1.2212 0.05434 0.04318 -0.0573 0.2836 1.0000
9.500 1.2325 0.05609 0.04501 -0.0562 0.2814 1.0000
9.750 1.2559 0.05718 0.04609 -0.0559 0.2794 1.0000
10.000 0.9665 0.09158 0.08115 -0.0610 0.2674 1.0000
10.250 0.9648 0.09609 0.08571 -0.0622 0.2650 1.0000
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Polar data table (+)
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