USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 50,000 Max Cl/Cd: 37.09 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usnps4-il-50000-n5.txt Download as CSV file: xf-usnps4-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USNPS4 (smoothed)
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
------ -------- --------- --------- -------- -------- --------
-6.500 -0.3840 0.10289 0.09703 -0.0189 1.0000 0.1024
-6.250 -0.3879 0.10034 0.09454 -0.0191 1.0000 0.1049
-6.000 -0.3927 0.09787 0.09210 -0.0219 1.0000 0.1088
-5.750 -0.3838 0.09420 0.08835 -0.0303 0.9972 0.1113
-5.500 -0.3674 0.08967 0.08389 -0.0285 0.9936 0.1138
-5.250 -0.3452 0.08576 0.07995 -0.0314 0.9878 0.1186
-5.000 -0.3172 0.08114 0.07517 -0.0403 0.9800 0.1289
-4.500 -0.2703 0.07384 0.06777 -0.0460 0.9672 0.1504
-4.250 -0.2062 0.06514 0.05809 -0.0601 0.9606 0.0795
-4.000 -0.1692 0.05966 0.05210 -0.0647 0.9541 0.0670
-3.750 -0.1375 0.05612 0.04842 -0.0676 0.9486 0.0651
-3.500 -0.1034 0.05285 0.04473 -0.0707 0.9411 0.0655
-3.250 -0.0636 0.04972 0.04107 -0.0743 0.9355 0.0660
-3.000 -0.0308 0.04700 0.03801 -0.0763 0.9277 0.0656
-2.750 0.0107 0.04431 0.03484 -0.0795 0.9225 0.0654
-2.500 0.0444 0.04231 0.03232 -0.0809 0.9136 0.0671
-2.250 0.0814 0.04041 0.03030 -0.0835 0.9071 0.0703
-2.000 0.1162 0.03880 0.02834 -0.0848 0.8983 0.0719
-1.750 0.1523 0.03735 0.02654 -0.0862 0.8900 0.0743
-1.500 0.1916 0.03613 0.02487 -0.0878 0.8820 0.0793
-1.250 0.2233 0.03493 0.02350 -0.0883 0.8718 0.0824
-1.000 0.2647 0.03374 0.02218 -0.0904 0.8653 0.0896
-0.750 0.2946 0.03304 0.02122 -0.0901 0.8535 0.0956
-0.500 0.3269 0.03219 0.02035 -0.0906 0.8428 0.1047
-0.250 0.3685 0.03111 0.01918 -0.0925 0.8355 0.1171
0.000 0.3984 0.03046 0.01848 -0.0926 0.8229 0.1337
0.250 0.4307 0.02969 0.01778 -0.0932 0.8111 0.1625
0.500 0.4666 0.02641 0.01688 -0.0934 0.8042 1.0000
0.750 0.4973 0.02625 0.01629 -0.0932 0.7908 1.0000
1.000 0.5278 0.02609 0.01583 -0.0931 0.7770 1.0000
1.250 0.5591 0.02590 0.01539 -0.0932 0.7632 1.0000
1.500 0.5914 0.02568 0.01496 -0.0934 0.7491 1.0000
1.750 0.6243 0.02546 0.01455 -0.0938 0.7346 1.0000
2.000 0.6575 0.02525 0.01416 -0.0942 0.7193 1.0000
2.250 0.6908 0.02507 0.01381 -0.0946 0.7031 1.0000
2.500 0.7240 0.02493 0.01351 -0.0951 0.6860 1.0000
2.750 0.7568 0.02482 0.01324 -0.0955 0.6681 1.0000
3.000 0.7897 0.02475 0.01300 -0.0959 0.6498 1.0000
3.250 0.8186 0.02484 0.01295 -0.0957 0.6300 1.0000
3.500 0.8457 0.02503 0.01300 -0.0953 0.6098 1.0000
3.750 0.8735 0.02523 0.01305 -0.0950 0.5900 1.0000
4.000 0.9014 0.02548 0.01314 -0.0948 0.5709 1.0000
4.250 0.9267 0.02583 0.01335 -0.0942 0.5519 1.0000
4.500 0.9504 0.02625 0.01367 -0.0934 0.5332 1.0000
4.750 0.9740 0.02671 0.01404 -0.0926 0.5153 1.0000
5.000 0.9974 0.02720 0.01442 -0.0919 0.4984 1.0000
5.250 1.0207 0.02772 0.01486 -0.0911 0.4825 1.0000
5.500 1.0435 0.02827 0.01533 -0.0903 0.4672 1.0000
5.750 1.0664 0.02885 0.01587 -0.0896 0.4528 1.0000
6.000 1.0897 0.02944 0.01639 -0.0889 0.4395 1.0000
6.250 1.1137 0.03003 0.01690 -0.0884 0.4268 1.0000
6.500 1.1341 0.03073 0.01762 -0.0874 0.4141 1.0000
6.750 1.1550 0.03145 0.01839 -0.0864 0.4024 1.0000
7.000 1.1775 0.03215 0.01907 -0.0858 0.3918 1.0000
7.250 1.1997 0.03286 0.01976 -0.0851 0.3815 1.0000
7.500 1.2184 0.03370 0.02071 -0.0839 0.3713 1.0000
7.750 1.2417 0.03444 0.02142 -0.0834 0.3626 1.0000
8.000 1.2594 0.03533 0.02243 -0.0821 0.3534 1.0000
8.250 1.2803 0.03618 0.02332 -0.0813 0.3453 1.0000
8.500 1.2985 0.03711 0.02437 -0.0801 0.3372 1.0000
8.750 1.3186 0.03804 0.02536 -0.0793 0.3300 1.0000
9.000 1.3343 0.03908 0.02654 -0.0778 0.3226 1.0000
9.250 1.3563 0.03998 0.02748 -0.0772 0.3162 1.0000
9.500 1.3661 0.04124 0.02897 -0.0749 0.3094 1.0000
9.750 1.3882 0.04216 0.02993 -0.0745 0.3037 1.0000
10.000 1.3974 0.04353 0.03151 -0.0722 0.2980 1.0000
10.250 1.4079 0.04484 0.03299 -0.0701 0.2922 1.0000
10.500 1.4337 0.04568 0.03386 -0.0702 0.2872 1.0000
10.750 1.4303 0.04761 0.03611 -0.0665 0.2822 1.0000
11.000 1.4369 0.04925 0.03796 -0.0642 0.2774 1.0000
11.250 1.4576 0.05031 0.03909 -0.0636 0.2731 1.0000
11.500 1.4563 0.05239 0.04143 -0.0606 0.2689 1.0000
11.750 1.4465 0.05494 0.04427 -0.0570 0.2646 1.0000
12.000 1.4520 0.05676 0.04626 -0.0551 0.2605 1.0000
12.250 1.4801 0.05747 0.04702 -0.0553 0.2568 1.0000
12.500 1.4459 0.06184 0.05175 -0.0504 0.2536 1.0000
12.750 1.4077 0.06721 0.05742 -0.0467 0.2503 1.0000
13.000 1.3770 0.07266 0.06309 -0.0447 0.2469 1.0000
13.250 1.3869 0.07449 0.06504 -0.0439 0.2436 1.0000
13.500 1.1365 0.11537 0.10593 -0.0557 0.2307 1.0000
13.750 1.1544 0.11571 0.10642 -0.0547 0.2283 1.0000
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Polar data table (+)
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