USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 200,000 Max Cl/Cd: 74.32 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usnps4-il-200000.txt Download as CSV file: xf-usnps4-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2506 0.10783 0.10487 -0.0312 0.9920 0.0370
-8.250 -0.2541 0.10388 0.10094 -0.0366 0.9881 0.0373
-8.000 -0.2550 0.09966 0.09672 -0.0418 0.9843 0.0375
-7.750 -0.2314 0.09415 0.09122 -0.0400 0.9816 0.0382
-7.500 -0.2144 0.09035 0.08741 -0.0410 0.9781 0.0395
-7.250 -0.2029 0.08615 0.08321 -0.0442 0.9753 0.0409
-7.000 -0.2014 0.08249 0.07957 -0.0460 0.9685 0.0420
-6.750 -0.3231 0.09063 0.08756 -0.0423 0.9794 0.0382
-6.500 -0.3029 0.08729 0.08422 -0.0434 0.9762 0.0393
-6.250 -0.2838 0.08330 0.08021 -0.0478 0.9697 0.0409
-6.000 -0.2555 0.07819 0.07503 -0.0560 0.9644 0.0430
-5.750 -0.2121 0.07113 0.06748 -0.0731 0.9540 0.0454
-5.500 -0.1947 0.06605 0.06255 -0.0738 0.9518 0.0462
-5.250 -0.1765 0.06306 0.05957 -0.0745 0.9457 0.0473
-5.000 -0.1483 0.05956 0.05600 -0.0778 0.9407 0.0493
-4.750 -0.0881 0.05588 0.05149 -0.0881 0.9373 0.0550
-4.500 -0.0786 0.05027 0.04612 -0.0880 0.9294 0.0564
-4.250 -0.0475 0.04751 0.04338 -0.0906 0.9260 0.0591
-4.000 0.0041 0.04425 0.03938 -0.0963 0.9236 0.0673
-3.750 0.0216 0.04078 0.03604 -0.0962 0.9150 0.0690
-3.500 0.0586 0.03813 0.03333 -0.0992 0.9119 0.0728
-3.250 0.1043 0.03516 0.02985 -0.1031 0.9098 0.0826
-3.000 0.1275 0.03328 0.02801 -0.1030 0.9011 0.0872
-2.750 0.1687 0.03090 0.02535 -0.1060 0.8979 0.0997
-2.500 0.2122 0.02876 0.02295 -0.1093 0.8959 0.1144
-2.250 0.2529 0.02466 0.01794 -0.1083 0.8897 0.0640
-2.000 0.2918 0.02264 0.01562 -0.1099 0.8852 0.0632
-1.750 0.3358 0.02058 0.01329 -0.1122 0.8829 0.0618
-1.500 0.3817 0.01908 0.01157 -0.1151 0.8810 0.0643
-1.250 0.4110 0.01813 0.01049 -0.1147 0.8718 0.0676
-1.000 0.4553 0.01672 0.00913 -0.1177 0.8681 0.0729
-0.750 0.4916 0.01605 0.00840 -0.1189 0.8601 0.0803
-0.500 0.5309 0.01490 0.00734 -0.1209 0.8527 0.0914
-0.250 0.5641 0.01416 0.00665 -0.1217 0.8413 0.1047
0.000 0.6013 0.01346 0.00598 -0.1233 0.8298 0.1309
0.250 0.6421 0.01093 0.00568 -0.1254 0.8190 1.0000
0.500 0.6736 0.01083 0.00536 -0.1258 0.8015 1.0000
0.750 0.7043 0.01078 0.00512 -0.1261 0.7823 1.0000
1.000 0.7350 0.01078 0.00492 -0.1264 0.7618 1.0000
1.250 0.7634 0.01085 0.00480 -0.1262 0.7399 1.0000
1.500 0.7895 0.01098 0.00474 -0.1256 0.7160 1.0000
1.750 0.8149 0.01115 0.00472 -0.1249 0.6918 1.0000
2.000 0.8389 0.01137 0.00474 -0.1240 0.6666 1.0000
2.250 0.8618 0.01161 0.00480 -0.1228 0.6411 1.0000
2.500 0.8844 0.01190 0.00489 -0.1216 0.6163 1.0000
2.750 0.9059 0.01220 0.00502 -0.1203 0.5909 1.0000
3.000 0.9273 0.01253 0.00517 -0.1189 0.5669 1.0000
3.250 0.9483 0.01286 0.00535 -0.1175 0.5433 1.0000
3.500 0.9692 0.01324 0.00555 -0.1161 0.5216 1.0000
3.750 0.9900 0.01359 0.00577 -0.1147 0.5001 1.0000
4.000 1.0108 0.01397 0.00601 -0.1134 0.4804 1.0000
4.250 1.0317 0.01436 0.00628 -0.1121 0.4623 1.0000
4.500 1.0525 0.01476 0.00656 -0.1108 0.4453 1.0000
4.750 1.0734 0.01516 0.00685 -0.1096 0.4293 1.0000
5.000 1.0943 0.01556 0.00716 -0.1083 0.4144 1.0000
5.250 1.1154 0.01596 0.00751 -0.1072 0.4006 1.0000
5.500 1.1365 0.01637 0.00785 -0.1060 0.3878 1.0000
5.750 1.1574 0.01681 0.00821 -0.1049 0.3760 1.0000
6.000 1.1783 0.01728 0.00857 -0.1037 0.3648 1.0000
6.250 1.1988 0.01766 0.00898 -0.1025 0.3537 1.0000
6.500 1.2200 0.01813 0.00939 -0.1015 0.3442 1.0000
6.750 1.2408 0.01859 0.00980 -0.1004 0.3351 1.0000
7.000 1.2611 0.01902 0.01027 -0.0991 0.3261 1.0000
7.250 1.2822 0.01957 0.01070 -0.0982 0.3180 1.0000
7.500 1.3006 0.01996 0.01118 -0.0966 0.3098 1.0000
7.750 1.3226 0.02053 0.01166 -0.0958 0.3027 1.0000
8.000 1.3413 0.02098 0.01221 -0.0943 0.2956 1.0000
8.250 1.3619 0.02151 0.01271 -0.0933 0.2892 1.0000
8.500 1.3822 0.02206 0.01330 -0.0923 0.2828 1.0000
8.750 1.4008 0.02255 0.01385 -0.0908 0.2765 1.0000
9.000 1.4238 0.02321 0.01445 -0.0904 0.2708 1.0000
9.250 1.4408 0.02372 0.01509 -0.0887 0.2653 1.0000
9.500 1.4605 0.02429 0.01569 -0.0876 0.2602 1.0000
9.750 1.4846 0.02501 0.01639 -0.0875 0.2554 1.0000
10.000 1.5005 0.02558 0.01712 -0.0857 0.2506 1.0000
10.250 1.5187 0.02617 0.01776 -0.0844 0.2458 1.0000
10.500 1.5445 0.02696 0.01849 -0.0846 0.2412 1.0000
10.750 1.5577 0.02760 0.01933 -0.0824 0.2373 1.0000
11.000 1.5750 0.02827 0.02012 -0.0810 0.2332 1.0000
11.250 1.5958 0.02896 0.02083 -0.0803 0.2295 1.0000
11.500 1.6199 0.02984 0.02176 -0.0803 0.2257 1.0000
11.750 1.6302 0.03060 0.02273 -0.0778 0.2221 1.0000
12.000 1.6428 0.03130 0.02354 -0.0758 0.2180 1.0000
12.250 1.6606 0.03197 0.02417 -0.0747 0.2134 1.0000
12.500 1.6650 0.03284 0.02523 -0.0715 0.2090 1.0000
12.750 1.6683 0.03362 0.02617 -0.0683 0.2042 1.0000
13.000 1.6783 0.03434 0.02686 -0.0662 0.1992 1.0000
13.250 1.6817 0.03541 0.02811 -0.0634 0.1948 1.0000
13.500 1.6841 0.03646 0.02934 -0.0605 0.1903 1.0000
13.750 1.6902 0.03745 0.03036 -0.0584 0.1859 1.0000
14.000 1.6940 0.03872 0.03177 -0.0561 0.1814 1.0000
14.250 1.6932 0.04017 0.03341 -0.0535 0.1767 1.0000
14.500 1.6955 0.04155 0.03486 -0.0515 0.1721 1.0000
14.750 1.6975 0.04318 0.03662 -0.0496 0.1678 1.0000
15.000 1.6963 0.04507 0.03873 -0.0477 0.1631 1.0000
15.250 1.6960 0.04699 0.04072 -0.0462 0.1583 1.0000
15.500 1.6946 0.04924 0.04316 -0.0449 0.1534 1.0000
15.750 1.6917 0.05179 0.04590 -0.0439 0.1476 1.0000
16.000 1.6872 0.05465 0.04886 -0.0431 0.1417 1.0000
16.250 1.6817 0.05794 0.05236 -0.0427 0.1337 1.0000
16.500 1.6736 0.06176 0.05633 -0.0427 0.1241 1.0000
16.750 1.6602 0.06648 0.06116 -0.0431 0.1113 1.0000
17.000 1.6392 0.07242 0.06713 -0.0439 0.0963 1.0000
17.250 1.6134 0.07927 0.07399 -0.0452 0.0809 1.0000
17.500 1.5852 0.08674 0.08149 -0.0469 0.0702 1.0000
17.750 1.5568 0.09449 0.08930 -0.0491 0.0632 1.0000
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