USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 50,000 Max Cl/Cd: 32.73 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usnps4-il-50000.txt Download as CSV file: xf-usnps4-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3456 0.11605 0.10984 -0.0216 1.0000 0.1554
-7.500 -0.3686 0.11568 0.10961 -0.0198 1.0000 0.1576
-7.250 -0.3938 0.11540 0.10949 -0.0197 1.0000 0.1587
-7.000 -0.3766 0.11005 0.10416 -0.0160 1.0000 0.1639
-6.750 -0.3807 0.10778 0.10197 -0.0144 1.0000 0.1695
-6.500 -0.3986 0.10659 0.10089 -0.0157 1.0000 0.1741
-6.250 -0.4050 0.10365 0.09804 -0.0159 1.0000 0.1773
-6.000 -0.3979 0.10043 0.09486 -0.0120 1.0000 0.1849
-5.250 -0.4086 0.09292 0.08749 -0.0164 1.0000 0.2095
-5.000 -0.4030 0.08966 0.08432 -0.0111 1.0000 0.2184
-4.750 -0.4013 0.08677 0.08147 -0.0114 1.0000 0.2304
-4.500 -0.3980 0.08405 0.07878 -0.0112 1.0000 0.2464
-4.250 -0.3941 0.08148 0.07625 -0.0098 1.0000 0.2650
-4.000 0.0557 0.05964 0.05358 -0.0278 1.0000 1.0000
-3.750 -0.3866 0.07657 0.07146 -0.0062 1.0000 0.3163
-3.500 -0.3841 0.07430 0.06926 -0.0031 1.0000 0.3493
-3.250 -0.3839 0.07225 0.06730 0.0006 1.0000 0.3940
-3.000 -0.1744 0.06494 0.05988 0.0245 1.0000 0.8756
-2.750 -0.2261 0.06510 0.06023 0.0336 1.0000 0.8433
-2.500 -0.3985 0.06682 0.06226 0.0243 1.0000 0.5441
-2.250 -0.4052 0.06503 0.06061 0.0342 1.0000 0.5964
-2.000 -0.4104 0.06322 0.05891 0.0438 1.0000 0.6495
-1.750 -0.4132 0.06131 0.05709 0.0524 1.0000 0.7017
-1.500 -0.4135 0.05926 0.05511 0.0571 1.0000 0.7393
-1.250 -0.1132 0.04987 0.04258 -0.0466 1.0000 0.2518
-1.000 -0.0323 0.04787 0.03937 -0.0561 0.9892 0.1873
-0.750 0.0404 0.04647 0.03717 -0.0640 0.9753 0.1685
-0.500 0.0985 0.04546 0.03557 -0.0694 0.9599 0.1634
-0.250 0.1500 0.04469 0.03446 -0.0737 0.9443 0.1666
0.000 0.2003 0.04413 0.03354 -0.0775 0.9287 0.1727
0.250 0.2493 0.04351 0.03273 -0.0808 0.9135 0.1841
0.500 0.2974 0.04297 0.03209 -0.0840 0.8983 0.2056
0.750 0.3458 0.04220 0.03147 -0.0874 0.8831 0.2450
1.000 0.3819 0.03946 0.03090 -0.0876 0.8682 1.0000
1.250 0.4283 0.03967 0.03028 -0.0899 0.8517 1.0000
1.500 0.4740 0.03968 0.02989 -0.0925 0.8354 1.0000
1.750 0.5027 0.03997 0.02996 -0.0927 0.8153 1.0000
2.000 0.5402 0.03995 0.02974 -0.0940 0.7973 1.0000
2.250 0.5798 0.03976 0.02937 -0.0954 0.7802 1.0000
2.500 0.6208 0.03935 0.02882 -0.0967 0.7638 1.0000
2.750 0.6621 0.03877 0.02812 -0.0978 0.7478 1.0000
3.000 0.7043 0.03796 0.02721 -0.0988 0.7325 1.0000
3.250 0.7489 0.03695 0.02611 -0.0999 0.7175 1.0000
3.500 0.7972 0.03581 0.02490 -0.1017 0.7024 1.0000
3.750 0.8481 0.03463 0.02364 -0.1039 0.6867 1.0000
4.000 0.8961 0.03362 0.02255 -0.1057 0.6701 1.0000
4.250 0.9434 0.03276 0.02162 -0.1075 0.6525 1.0000
4.500 0.9897 0.03210 0.02084 -0.1094 0.6344 1.0000
4.750 1.0260 0.03207 0.02072 -0.1100 0.6157 1.0000
5.000 1.0486 0.03269 0.02131 -0.1088 0.5963 1.0000
5.250 1.0758 0.03321 0.02176 -0.1083 0.5783 1.0000
5.500 1.1029 0.03379 0.02231 -0.1078 0.5611 1.0000
5.750 1.1286 0.03448 0.02295 -0.1072 0.5449 1.0000
6.000 1.1525 0.03532 0.02377 -0.1064 0.5296 1.0000
6.250 1.1755 0.03625 0.02469 -0.1056 0.5153 1.0000
6.500 1.1996 0.03718 0.02562 -0.1049 0.5018 1.0000
6.750 1.2288 0.03796 0.02635 -0.1050 0.4893 1.0000
7.000 1.2435 0.03934 0.02782 -0.1031 0.4770 1.0000
7.250 1.2524 0.04108 0.02970 -0.1006 0.4658 1.0000
7.500 1.2747 0.04230 0.03096 -0.0998 0.4555 1.0000
7.750 1.2922 0.04374 0.03248 -0.0985 0.4455 1.0000
8.000 1.2914 0.04614 0.03509 -0.0949 0.4367 1.0000
8.250 1.3325 0.04658 0.03546 -0.0967 0.4273 1.0000
8.500 1.2998 0.05064 0.03987 -0.0894 0.4203 1.0000
8.750 1.3415 0.05113 0.04036 -0.0912 0.4122 1.0000
9.000 1.2912 0.05656 0.04612 -0.0828 0.4072 1.0000
9.250 0.9682 0.09425 0.08388 -0.0740 0.4073 1.0000
9.500 0.9302 0.10374 0.09336 -0.0758 0.4064 1.0000
9.750 0.9103 0.11082 0.10049 -0.0772 0.4065 1.0000
10.000 0.9020 0.11679 0.10651 -0.0785 0.4085 1.0000
10.250 0.9160 0.12114 0.11097 -0.0796 0.4115 1.0000
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