USA-35B AIRFOIL (usa35b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA-35B AIRFOIL (usa35b-il) Reynolds number: 100,000 Max Cl/Cd: 56.73 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa35b-il-100000-n5.txt Download as CSV file: xf-usa35b-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA-35B 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3516 0.09586 0.09083 -0.0403 1.0000 0.0803
-9.750 -0.3655 0.09363 0.08871 -0.0395 1.0000 0.0804
-9.500 -0.3821 0.08551 0.08063 -0.0401 1.0000 0.0605
-9.250 -0.3844 0.08368 0.07887 -0.0377 1.0000 0.0609
-9.000 -0.3723 0.08104 0.07625 -0.0386 0.9963 0.0617
-8.500 -0.3372 0.06105 0.05583 -0.0645 0.9745 0.0520
-8.250 -0.3137 0.05627 0.05089 -0.0696 0.9664 0.0514
-8.000 -0.2875 0.05059 0.04495 -0.0756 0.9590 0.0509
-7.750 -0.2643 0.04519 0.03919 -0.0800 0.9493 0.0505
-7.500 -0.2362 0.03953 0.03292 -0.0846 0.9421 0.0512
-7.250 -0.2119 0.03546 0.02826 -0.0866 0.9315 0.0518
-7.000 -0.1824 0.03243 0.02475 -0.0884 0.9235 0.0519
-6.750 -0.1538 0.02996 0.02182 -0.0894 0.9140 0.0522
-6.500 -0.1244 0.02800 0.01954 -0.0902 0.9048 0.0526
-6.250 -0.0936 0.02646 0.01780 -0.0911 0.8957 0.0532
-6.000 -0.0652 0.02523 0.01639 -0.0914 0.8845 0.0540
-5.750 -0.0337 0.02419 0.01519 -0.0921 0.8753 0.0556
-5.500 -0.0053 0.02320 0.01401 -0.0921 0.8632 0.0574
-5.250 0.0235 0.02218 0.01275 -0.0920 0.8513 0.0589
-5.000 0.0534 0.02120 0.01154 -0.0920 0.8403 0.0600
-4.750 0.0818 0.02034 0.01064 -0.0919 0.8279 0.0613
-4.500 0.1092 0.01969 0.00996 -0.0916 0.8146 0.0629
-4.250 0.1372 0.01911 0.00932 -0.0914 0.8020 0.0653
-4.000 0.1656 0.01860 0.00869 -0.0911 0.7900 0.0691
-3.750 0.1928 0.01809 0.00820 -0.0908 0.7771 0.0730
-3.500 0.2199 0.01767 0.00774 -0.0904 0.7641 0.0778
-3.250 0.2472 0.01723 0.00726 -0.0900 0.7522 0.0839
-3.000 0.2750 0.01685 0.00683 -0.0897 0.7413 0.0952
-2.750 0.3017 0.01647 0.00652 -0.0894 0.7289 0.1150
-2.500 0.3288 0.01609 0.00629 -0.0891 0.7176 0.1547
-2.250 0.3558 0.01561 0.00609 -0.0889 0.7067 0.2481
-2.000 0.3790 0.01466 0.00611 -0.0881 0.6947 0.5139
-1.750 0.4067 0.01363 0.00612 -0.0863 0.6832 0.9080
-1.500 0.4455 0.01364 0.00589 -0.0883 0.6722 1.0000
-1.250 0.4721 0.01378 0.00583 -0.0878 0.6617 1.0000
-1.000 0.4989 0.01394 0.00580 -0.0875 0.6524 1.0000
-0.750 0.5258 0.01411 0.00579 -0.0871 0.6435 1.0000
-0.500 0.5525 0.01429 0.00584 -0.0867 0.6345 1.0000
-0.250 0.5795 0.01447 0.00587 -0.0864 0.6260 1.0000
0.000 0.6061 0.01467 0.00597 -0.0861 0.6174 1.0000
0.250 0.6330 0.01487 0.00605 -0.0857 0.6090 1.0000
0.500 0.6596 0.01509 0.00619 -0.0854 0.6006 1.0000
0.750 0.6863 0.01530 0.00631 -0.0850 0.5921 1.0000
1.000 0.7128 0.01553 0.00648 -0.0847 0.5837 1.0000
1.250 0.7394 0.01575 0.00664 -0.0843 0.5752 1.0000
1.500 0.7657 0.01599 0.00684 -0.0839 0.5666 1.0000
1.750 0.7920 0.01622 0.00702 -0.0835 0.5578 1.0000
2.000 0.8181 0.01647 0.00725 -0.0831 0.5489 1.0000
2.250 0.8442 0.01670 0.00745 -0.0826 0.5399 1.0000
2.500 0.8698 0.01695 0.00771 -0.0822 0.5302 1.0000
2.750 0.8958 0.01718 0.00787 -0.0816 0.5206 1.0000
3.000 0.9202 0.01740 0.00812 -0.0809 0.5071 1.0000
3.250 0.9444 0.01760 0.00831 -0.0801 0.4927 1.0000
3.500 0.9686 0.01782 0.00851 -0.0794 0.4785 1.0000
3.750 0.9930 0.01807 0.00875 -0.0786 0.4657 1.0000
4.000 1.0173 0.01833 0.00898 -0.0779 0.4536 1.0000
4.250 1.0411 0.01862 0.00931 -0.0772 0.4402 1.0000
4.500 1.0647 0.01892 0.00965 -0.0764 0.4270 1.0000
4.750 1.0881 0.01925 0.00999 -0.0756 0.4140 1.0000
5.000 1.1110 0.01960 0.01034 -0.0747 0.4010 1.0000
5.250 1.1335 0.01998 0.01072 -0.0738 0.3882 1.0000
5.500 1.1557 0.02040 0.01114 -0.0728 0.3754 1.0000
5.750 1.1775 0.02085 0.01162 -0.0719 0.3628 1.0000
6.000 1.1989 0.02134 0.01213 -0.0708 0.3508 1.0000
6.250 1.2196 0.02186 0.01265 -0.0697 0.3391 1.0000
6.500 1.2395 0.02243 0.01322 -0.0685 0.3268 1.0000
6.750 1.2584 0.02302 0.01384 -0.0672 0.3128 1.0000
7.000 1.2758 0.02367 0.01451 -0.0657 0.2976 1.0000
7.250 1.2920 0.02435 0.01519 -0.0641 0.2820 1.0000
7.500 1.3074 0.02507 0.01592 -0.0624 0.2670 1.0000
7.750 1.3221 0.02582 0.01669 -0.0606 0.2530 1.0000
8.000 1.3357 0.02661 0.01752 -0.0588 0.2402 1.0000
8.250 1.3469 0.02745 0.01837 -0.0566 0.2286 1.0000
8.500 1.3577 0.02833 0.01930 -0.0544 0.2178 1.0000
8.750 1.3680 0.02929 0.02032 -0.0523 0.2074 1.0000
9.000 1.3760 0.03039 0.02146 -0.0502 0.1970 1.0000
9.250 1.3826 0.03165 0.02272 -0.0480 0.1868 1.0000
9.500 1.3904 0.03292 0.02408 -0.0462 0.1773 1.0000
9.750 1.3955 0.03442 0.02562 -0.0444 0.1683 1.0000
10.000 1.3997 0.03607 0.02732 -0.0427 0.1593 1.0000
10.250 1.4042 0.03780 0.02917 -0.0412 0.1502 1.0000
10.500 1.4053 0.03988 0.03129 -0.0398 0.1416 1.0000
10.750 1.4067 0.04208 0.03359 -0.0386 0.1316 1.0000
11.000 1.4067 0.04453 0.03614 -0.0377 0.1212 1.0000
11.250 1.4041 0.04736 0.03904 -0.0370 0.1109 1.0000
11.500 1.3995 0.05054 0.04228 -0.0366 0.1010 1.0000
11.750 1.3942 0.05396 0.04575 -0.0364 0.0914 1.0000
12.000 1.3885 0.05753 0.04939 -0.0364 0.0831 1.0000
12.250 1.3806 0.06147 0.05340 -0.0366 0.0775 1.0000
12.500 1.3717 0.06565 0.05763 -0.0370 0.0731 1.0000
12.750 1.3618 0.07009 0.06211 -0.0377 0.0700 1.0000
13.000 1.3535 0.07443 0.06654 -0.0384 0.0672 1.0000
13.250 1.3439 0.07905 0.07125 -0.0393 0.0649 1.0000
13.500 1.3335 0.08389 0.07614 -0.0404 0.0631 1.0000
13.750 1.3250 0.08850 0.08082 -0.0414 0.0613 1.0000
14.000 1.3191 0.09281 0.08526 -0.0424 0.0594 1.0000
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Polar data table (+)
Polar graphs
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