USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 40 B AIRFOIL (usa40b-il) Reynolds number: 100,000 Max Cl/Cd: 45.34 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa40b-il-100000-n5.txt Download as CSV file: xf-usa40b-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3027 0.09235 0.08707 -0.0363 1.0000 0.0544
-8.750 -0.3074 0.08892 0.08371 -0.0368 1.0000 0.0543
-8.500 -0.3148 0.08547 0.08034 -0.0372 1.0000 0.0542
-8.250 -0.3250 0.08212 0.07708 -0.0372 1.0000 0.0540
-8.000 -0.3401 0.07886 0.07393 -0.0367 1.0000 0.0536
-7.500 -0.4392 0.04656 0.04066 -0.0665 0.9856 0.0498
-7.250 -0.4129 0.04218 0.03593 -0.0716 0.9769 0.0500
-7.000 -0.3813 0.03890 0.03235 -0.0757 0.9698 0.0504
-6.750 -0.3526 0.03625 0.02942 -0.0783 0.9603 0.0509
-6.500 -0.3209 0.03400 0.02691 -0.0809 0.9518 0.0517
-6.250 -0.2859 0.03192 0.02455 -0.0837 0.9436 0.0530
-6.000 -0.2512 0.02971 0.02192 -0.0860 0.9319 0.0545
-5.750 -0.2119 0.02752 0.01928 -0.0886 0.9206 0.0556
-5.500 -0.1715 0.02579 0.01731 -0.0910 0.9091 0.0565
-5.250 -0.1388 0.02464 0.01610 -0.0919 0.8947 0.0576
-5.000 -0.1055 0.02358 0.01494 -0.0928 0.8819 0.0589
-4.750 -0.0694 0.02255 0.01375 -0.0942 0.8702 0.0609
-4.500 -0.0377 0.02168 0.01271 -0.0946 0.8548 0.0634
-4.250 -0.0068 0.02093 0.01200 -0.0950 0.8385 0.0657
-4.000 0.0247 0.02020 0.01119 -0.0953 0.8216 0.0684
-3.750 0.0561 0.01950 0.01035 -0.0955 0.8039 0.0714
-3.500 0.0868 0.01884 0.00970 -0.0957 0.7853 0.0749
-3.250 0.1175 0.01832 0.00905 -0.0957 0.7662 0.0809
-3.000 0.1469 0.01781 0.00850 -0.0957 0.7469 0.0880
-2.750 0.1756 0.01734 0.00796 -0.0955 0.7271 0.0970
-2.500 0.2034 0.01695 0.00754 -0.0952 0.7069 0.1108
-2.250 0.2303 0.01660 0.00724 -0.0947 0.6864 0.1332
-2.000 0.2563 0.01631 0.00707 -0.0941 0.6645 0.1754
-1.750 0.2816 0.01606 0.00691 -0.0934 0.6407 0.2257
-1.500 0.3065 0.01580 0.00676 -0.0927 0.6155 0.2755
-1.250 0.3314 0.01561 0.00665 -0.0918 0.5885 0.3312
-1.000 0.3560 0.01547 0.00656 -0.0909 0.5597 0.3920
-0.750 0.3795 0.01537 0.00652 -0.0898 0.5312 0.4590
-0.500 0.4019 0.01531 0.00662 -0.0882 0.5041 0.5459
-0.250 0.4233 0.01541 0.00678 -0.0863 0.4799 0.6317
0.000 0.4453 0.01560 0.00690 -0.0845 0.4584 0.6892
0.250 0.4679 0.01580 0.00698 -0.0829 0.4400 0.7308
0.500 0.4907 0.01600 0.00704 -0.0815 0.4243 0.7622
0.750 0.5145 0.01618 0.00710 -0.0803 0.4102 0.7892
1.000 0.5382 0.01632 0.00714 -0.0791 0.3978 0.8135
1.250 0.5621 0.01648 0.00717 -0.0779 0.3869 0.8399
1.500 0.5880 0.01654 0.00722 -0.0772 0.3761 0.8721
1.750 0.6288 0.01662 0.00724 -0.0795 0.3657 0.9909
2.000 0.6554 0.01694 0.00742 -0.0793 0.3572 1.0000
2.250 0.6821 0.01731 0.00758 -0.0792 0.3500 1.0000
2.500 0.7092 0.01763 0.00781 -0.0790 0.3421 1.0000
2.750 0.7356 0.01800 0.00801 -0.0788 0.3354 1.0000
3.000 0.7622 0.01837 0.00826 -0.0786 0.3292 1.0000
3.250 0.7888 0.01872 0.00854 -0.0783 0.3229 1.0000
3.500 0.8150 0.01912 0.00881 -0.0780 0.3177 1.0000
3.750 0.8414 0.01955 0.00911 -0.0778 0.3132 1.0000
4.000 0.8677 0.01993 0.00948 -0.0775 0.3080 1.0000
4.250 0.8937 0.02034 0.00983 -0.0772 0.3031 1.0000
4.500 0.9195 0.02078 0.01015 -0.0768 0.2989 1.0000
4.750 0.9455 0.02124 0.01055 -0.0765 0.2949 1.0000
5.000 0.9710 0.02168 0.01101 -0.0761 0.2905 1.0000
5.250 0.9965 0.02213 0.01144 -0.0757 0.2865 1.0000
5.500 1.0220 0.02261 0.01187 -0.0753 0.2832 1.0000
5.750 1.0477 0.02313 0.01231 -0.0750 0.2803 1.0000
6.000 1.0731 0.02368 0.01286 -0.0747 0.2774 1.0000
6.250 1.0976 0.02421 0.01346 -0.0742 0.2741 1.0000
6.500 1.1220 0.02476 0.01404 -0.0737 0.2708 1.0000
6.750 1.1464 0.02529 0.01459 -0.0732 0.2678 1.0000
7.000 1.1709 0.02583 0.01510 -0.0727 0.2650 1.0000
7.250 1.1960 0.02642 0.01563 -0.0724 0.2627 1.0000
7.500 1.2197 0.02709 0.01636 -0.0719 0.2604 1.0000
7.750 1.2421 0.02778 0.01719 -0.0712 0.2579 1.0000
8.000 1.2644 0.02849 0.01800 -0.0705 0.2554 1.0000
8.250 1.2868 0.02920 0.01879 -0.0698 0.2531 1.0000
8.500 1.3093 0.02991 0.01957 -0.0692 0.2510 1.0000
8.750 1.3320 0.03061 0.02029 -0.0685 0.2490 1.0000
9.000 1.3553 0.03128 0.02097 -0.0680 0.2470 1.0000
9.250 1.3798 0.03201 0.02168 -0.0677 0.2452 1.0000
9.500 1.3967 0.03297 0.02284 -0.0664 0.2430 1.0000
9.750 1.4130 0.03397 0.02403 -0.0651 0.2408 1.0000
10.000 1.4292 0.03496 0.02520 -0.0638 0.2385 1.0000
10.250 1.4455 0.03589 0.02627 -0.0625 0.2363 1.0000
10.500 1.4629 0.03674 0.02721 -0.0614 0.2341 1.0000
10.750 1.4821 0.03747 0.02798 -0.0604 0.2319 1.0000
11.000 1.5048 0.03804 0.02853 -0.0599 0.2297 1.0000
11.250 1.5174 0.03908 0.02970 -0.0583 0.2273 1.0000
11.500 1.5186 0.04050 0.03139 -0.0554 0.2247 1.0000
11.750 1.5204 0.04182 0.03292 -0.0525 0.2223 1.0000
12.000 1.5235 0.04308 0.03434 -0.0500 0.2201 1.0000
12.250 1.5304 0.04415 0.03550 -0.0479 0.2178 1.0000
12.500 1.5452 0.04482 0.03620 -0.0466 0.2155 1.0000
12.750 1.5680 0.04527 0.03661 -0.0461 0.2134 1.0000
13.000 1.5588 0.04735 0.03892 -0.0432 0.2115 1.0000
13.250 1.5340 0.05060 0.04248 -0.0400 0.2096 1.0000
13.500 1.5051 0.05469 0.04685 -0.0379 0.2074 1.0000
13.750 1.4688 0.06014 0.05256 -0.0372 0.2051 1.0000
14.000 1.4226 0.06764 0.06030 -0.0383 0.2026 1.0000
14.250 1.4074 0.07229 0.06507 -0.0393 0.2004 1.0000
14.500 1.4513 0.06974 0.06249 -0.0375 0.1989 1.0000
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