USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 100,000 Max Cl/Cd: 53.17 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usnps4-il-100000-n5.txt Download as CSV file: xf-usnps4-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3394 0.11972 0.11504 -0.0281 1.0000 0.0449
-8.500 -0.3505 0.11795 0.11335 -0.0276 1.0000 0.0450
-8.250 -0.3629 0.11621 0.11169 -0.0266 1.0000 0.0451
-8.000 -0.3598 0.11269 0.10820 -0.0320 0.9952 0.0452
-7.750 -0.3493 0.10805 0.10358 -0.0380 0.9898 0.0454
-7.500 -0.3323 0.10358 0.09911 -0.0340 0.9891 0.0462
-7.250 -0.3172 0.09975 0.09527 -0.0360 0.9858 0.0471
-7.000 -0.3048 0.09595 0.09147 -0.0391 0.9802 0.0480
-6.750 -0.2875 0.09165 0.08717 -0.0444 0.9753 0.0492
-6.500 -0.2736 0.08749 0.08299 -0.0489 0.9680 0.0504
-6.250 -0.1800 0.06819 0.06385 -0.0673 0.9384 0.0557
-6.000 -0.1683 0.06526 0.06098 -0.0645 0.9330 0.0577
-5.750 -0.1559 0.06134 0.05701 -0.0667 0.9268 0.0597
-5.500 -0.1362 0.05636 0.05193 -0.0717 0.9231 0.0615
-5.250 -0.1275 0.05268 0.04816 -0.0736 0.9137 0.0627
-4.750 -0.1027 0.05081 0.04493 -0.0856 0.9251 0.0374
-4.500 -0.0776 0.04728 0.04116 -0.0871 0.9186 0.0373
-4.250 -0.0522 0.04546 0.03937 -0.0885 0.9129 0.0395
-4.000 -0.0157 0.04218 0.03579 -0.0917 0.9096 0.0408
-3.750 0.0095 0.03893 0.03214 -0.0920 0.9011 0.0400
-3.500 0.0467 0.03553 0.02825 -0.0943 0.8970 0.0396
-3.250 0.0785 0.03318 0.02552 -0.0953 0.8909 0.0403
-3.000 0.1110 0.03129 0.02324 -0.0962 0.8843 0.0427
-2.750 0.1512 0.02903 0.02047 -0.0982 0.8809 0.0441
-2.500 0.1790 0.02751 0.01855 -0.0978 0.8719 0.0449
-2.250 0.2162 0.02596 0.01683 -0.0995 0.8673 0.0469
-2.000 0.2450 0.02511 0.01589 -0.0995 0.8585 0.0501
-1.750 0.2815 0.02384 0.01439 -0.1006 0.8528 0.0529
-1.500 0.3121 0.02283 0.01323 -0.1007 0.8441 0.0555
-1.250 0.3479 0.02188 0.01231 -0.1020 0.8372 0.0608
-1.000 0.3773 0.02115 0.01150 -0.1019 0.8268 0.0653
-0.750 0.4166 0.02016 0.01057 -0.1038 0.8202 0.0729
-0.500 0.4456 0.01965 0.00996 -0.1037 0.8078 0.0802
-0.250 0.4781 0.01904 0.00936 -0.1043 0.7959 0.0918
0.000 0.5144 0.01846 0.00872 -0.1057 0.7840 0.1093
0.250 0.5523 0.01775 0.00817 -0.1075 0.7712 0.1615
0.750 0.6214 0.01541 0.00758 -0.1090 0.7402 1.0000
1.000 0.6537 0.01538 0.00732 -0.1096 0.7211 1.0000
1.250 0.6863 0.01538 0.00709 -0.1103 0.7010 1.0000
1.750 0.7469 0.01556 0.00683 -0.1109 0.6574 1.0000
2.000 0.7753 0.01572 0.00678 -0.1108 0.6349 1.0000
2.250 0.8016 0.01593 0.00679 -0.1104 0.6121 1.0000
2.500 0.8270 0.01618 0.00685 -0.1099 0.5894 1.0000
2.750 0.8518 0.01646 0.00694 -0.1092 0.5677 1.0000
3.000 0.8753 0.01676 0.00708 -0.1083 0.5460 1.0000
3.250 0.8986 0.01709 0.00725 -0.1074 0.5254 1.0000
3.500 0.9215 0.01745 0.00744 -0.1065 0.5063 1.0000
3.750 0.9437 0.01781 0.00768 -0.1054 0.4874 1.0000
4.000 0.9657 0.01819 0.00793 -0.1044 0.4697 1.0000
4.250 0.9876 0.01858 0.00821 -0.1033 0.4532 1.0000
4.500 1.0092 0.01898 0.00852 -0.1022 0.4376 1.0000
4.750 1.0305 0.01940 0.00884 -0.1011 0.4230 1.0000
5.000 1.0517 0.01984 0.00918 -0.1000 0.4095 1.0000
5.250 1.0727 0.02028 0.00955 -0.0989 0.3965 1.0000
5.500 1.0936 0.02072 0.00996 -0.0978 0.3840 1.0000
5.750 1.1144 0.02117 0.01037 -0.0966 0.3726 1.0000
6.000 1.1348 0.02166 0.01079 -0.0954 0.3623 1.0000
6.250 1.1550 0.02213 0.01124 -0.0942 0.3519 1.0000
6.500 1.1752 0.02262 0.01174 -0.0931 0.3422 1.0000
6.750 1.1945 0.02315 0.01221 -0.0917 0.3337 1.0000
7.000 1.2140 0.02363 0.01274 -0.0905 0.3249 1.0000
7.250 1.2325 0.02419 0.01325 -0.0890 0.3175 1.0000
7.500 1.2514 0.02471 0.01384 -0.0877 0.3091 1.0000
7.750 1.2696 0.02530 0.01439 -0.0863 0.3024 1.0000
8.000 1.2885 0.02586 0.01504 -0.0850 0.2950 1.0000
8.250 1.3068 0.02647 0.01567 -0.0836 0.2889 1.0000
8.500 1.3253 0.02709 0.01635 -0.0824 0.2826 1.0000
8.750 1.3429 0.02772 0.01704 -0.0809 0.2763 1.0000
9.000 1.3608 0.02840 0.01770 -0.0796 0.2710 1.0000
9.250 1.3781 0.02908 0.01853 -0.0782 0.2650 1.0000
9.500 1.3954 0.02978 0.01929 -0.0769 0.2600 1.0000
9.750 1.4136 0.03052 0.02004 -0.0757 0.2556 1.0000
10.000 1.4296 0.03128 0.02099 -0.0742 0.2504 1.0000
10.250 1.4455 0.03205 0.02184 -0.0727 0.2456 1.0000
10.500 1.4630 0.03284 0.02261 -0.0716 0.2416 1.0000
10.750 1.4770 0.03372 0.02371 -0.0699 0.2370 1.0000
11.000 1.4921 0.03460 0.02474 -0.0684 0.2328 1.0000
11.250 1.5080 0.03547 0.02568 -0.0671 0.2293 1.0000
11.500 1.5244 0.03638 0.02666 -0.0659 0.2259 1.0000
11.750 1.5355 0.03746 0.02797 -0.0640 0.2218 1.0000
12.000 1.5474 0.03850 0.02917 -0.0623 0.2180 1.0000
12.250 1.5612 0.03948 0.03025 -0.0609 0.2147 1.0000
12.500 1.5776 0.04048 0.03131 -0.0599 0.2119 1.0000
12.750 1.5847 0.04187 0.03298 -0.0578 0.2087 1.0000
13.000 1.5928 0.04322 0.03455 -0.0559 0.2053 1.0000
13.250 1.6023 0.04448 0.03597 -0.0542 0.2022 1.0000
13.500 1.6150 0.04559 0.03716 -0.0530 0.1993 1.0000
13.750 1.6202 0.04713 0.03890 -0.0510 0.1962 1.0000
14.000 1.6167 0.04912 0.04117 -0.0485 0.1924 1.0000
14.250 1.6161 0.05081 0.04302 -0.0464 0.1879 1.0000
14.500 1.6186 0.05222 0.04443 -0.0446 0.1832 1.0000
14.750 1.6052 0.05516 0.04771 -0.0424 0.1786 1.0000
15.000 1.5980 0.05759 0.05030 -0.0408 0.1734 1.0000
15.250 1.5917 0.06013 0.05293 -0.0395 0.1684 1.0000
15.500 1.5773 0.06397 0.05705 -0.0386 0.1636 1.0000
15.750 1.5687 0.06727 0.06048 -0.0382 0.1586 1.0000
16.000 1.5572 0.07127 0.06464 -0.0381 0.1541 1.0000
16.250 1.5406 0.07632 0.06995 -0.0387 0.1497 1.0000
16.500 1.5285 0.08088 0.07465 -0.0395 0.1453 1.0000
16.750 1.5142 0.08603 0.07996 -0.0406 0.1416 1.0000
17.000 1.4900 0.09308 0.08728 -0.0428 0.1384 1.0000
17.250 1.4660 0.10036 0.09477 -0.0453 0.1352 1.0000
17.500 1.4531 0.10586 0.10034 -0.0474 0.1312 1.0000
17.750 1.4209 0.11515 0.10983 -0.0514 0.1289 1.0000
18.000 1.3708 0.12827 0.12316 -0.0576 0.1277 1.0000
|
Polar data table (+)
Polar graphs
<< Back to USNPS4 (smoothed) (usnps4-il)