USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 500,000 Max Cl/Cd: 95.24 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usnps4-il-500000.txt Download as CSV file: xf-usnps4-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2144 0.09187 0.08965 -0.0591 0.9791 0.0201
-7.750 -0.2055 0.08656 0.08435 -0.0671 0.9757 0.0212
-7.500 -0.1966 0.07968 0.07745 -0.0783 0.9668 0.0214
-7.250 -0.1796 0.07409 0.07185 -0.0839 0.9647 0.0217
-7.000 -0.1580 0.07104 0.06879 -0.0866 0.9635 0.0220
-6.750 -0.1475 0.06815 0.06589 -0.0878 0.9567 0.0223
-6.500 -0.1232 0.06413 0.06183 -0.0932 0.9538 0.0229
-6.250 -0.0937 0.05929 0.05691 -0.1002 0.9518 0.0241
-5.750 -0.0451 0.04744 0.04471 -0.1110 0.9414 0.0266
-5.500 -0.0149 0.04469 0.04190 -0.1142 0.9397 0.0272
-5.250 0.0193 0.04122 0.03830 -0.1182 0.9385 0.0287
-5.000 0.0738 0.01839 0.01522 -0.1201 0.9262 0.0320
-4.750 0.1056 0.01630 0.01306 -0.1227 0.9247 0.0330
-4.500 0.1377 0.01399 0.01056 -0.1248 0.9226 0.0354
-4.250 0.1548 0.01127 0.00740 -0.1234 0.9144 0.0386
-4.000 0.1873 0.00983 0.00590 -0.1254 0.9112 0.0398
-3.750 0.2057 0.01802 0.01297 -0.1272 0.9175 0.0299
-3.500 0.2389 0.01587 0.01043 -0.1280 0.9133 0.0303
-3.250 0.2767 0.01461 0.00888 -0.1298 0.9102 0.0311
-3.000 0.3027 0.01307 0.00718 -0.1293 0.9021 0.0319
-2.750 0.3378 0.01229 0.00637 -0.1308 0.8964 0.0331
-2.500 0.3667 0.01179 0.00582 -0.1309 0.8868 0.0346
-2.250 0.4020 0.01133 0.00527 -0.1323 0.8789 0.0368
-2.000 0.4313 0.01065 0.00452 -0.1325 0.8672 0.0386
-1.750 0.4609 0.01029 0.00415 -0.1327 0.8541 0.0411
-1.500 0.4908 0.01005 0.00384 -0.1330 0.8397 0.0442
-1.250 0.5196 0.00972 0.00345 -0.1331 0.8235 0.0486
-1.000 0.5481 0.00961 0.00326 -0.1331 0.8059 0.0535
-0.750 0.5749 0.00942 0.00300 -0.1328 0.7866 0.0595
-0.500 0.6012 0.00941 0.00290 -0.1323 0.7655 0.0662
-0.250 0.6267 0.00934 0.00274 -0.1317 0.7439 0.0768
0.000 0.6516 0.00931 0.00264 -0.1310 0.7212 0.0917
0.250 0.6749 0.00884 0.00263 -0.1304 0.6983 0.3007
0.500 0.7020 0.00742 0.00288 -0.1301 0.6750 1.0000
0.750 0.7236 0.00762 0.00289 -0.1287 0.6508 1.0000
1.000 0.7457 0.00783 0.00292 -0.1274 0.6269 1.0000
1.250 0.7673 0.00806 0.00298 -0.1260 0.6026 1.0000
1.500 0.7895 0.00829 0.00305 -0.1248 0.5784 1.0000
1.750 0.8115 0.00854 0.00314 -0.1236 0.5554 1.0000
2.000 0.8340 0.00879 0.00324 -0.1225 0.5329 1.0000
2.250 0.8562 0.00905 0.00335 -0.1214 0.5104 1.0000
2.500 0.8784 0.00932 0.00348 -0.1203 0.4895 1.0000
2.750 0.9014 0.00957 0.00361 -0.1193 0.4700 1.0000
3.000 0.9242 0.00983 0.00376 -0.1184 0.4512 1.0000
3.250 0.9468 0.01010 0.00391 -0.1174 0.4330 1.0000
3.500 0.9695 0.01037 0.00408 -0.1164 0.4162 1.0000
3.750 0.9923 0.01063 0.00426 -0.1155 0.4009 1.0000
4.000 1.0152 0.01090 0.00444 -0.1146 0.3868 1.0000
4.250 1.0378 0.01117 0.00464 -0.1137 0.3732 1.0000
4.500 1.0602 0.01145 0.00484 -0.1127 0.3602 1.0000
4.750 1.0820 0.01175 0.00505 -0.1117 0.3482 1.0000
5.000 1.1043 0.01200 0.00526 -0.1107 0.3371 1.0000
5.250 1.1260 0.01227 0.00549 -0.1096 0.3272 1.0000
5.500 1.1464 0.01260 0.00575 -0.1083 0.3175 1.0000
5.750 1.1686 0.01285 0.00599 -0.1073 0.3081 1.0000
6.000 1.1895 0.01317 0.00627 -0.1061 0.2994 1.0000
6.250 1.2109 0.01347 0.00654 -0.1050 0.2910 1.0000
6.500 1.2320 0.01379 0.00684 -0.1039 0.2836 1.0000
6.750 1.2532 0.01410 0.00713 -0.1028 0.2762 1.0000
7.000 1.2737 0.01446 0.00747 -0.1016 0.2696 1.0000
7.250 1.2950 0.01476 0.00779 -0.1006 0.2629 1.0000
7.500 1.3140 0.01520 0.00817 -0.0992 0.2563 1.0000
7.750 1.3359 0.01547 0.00850 -0.0983 0.2504 1.0000
8.000 1.3552 0.01588 0.00889 -0.0970 0.2446 1.0000
8.250 1.3749 0.01628 0.00930 -0.0957 0.2395 1.0000
8.500 1.3954 0.01663 0.00968 -0.0946 0.2345 1.0000
8.750 1.4138 0.01709 0.01014 -0.0932 0.2296 1.0000
9.000 1.4324 0.01755 0.01061 -0.0919 0.2251 1.0000
9.250 1.4525 0.01792 0.01104 -0.0908 0.2205 1.0000
9.500 1.4703 0.01840 0.01153 -0.0894 0.2160 1.0000
9.750 1.4866 0.01900 0.01213 -0.0877 0.2117 1.0000
10.000 1.5063 0.01939 0.01260 -0.0866 0.2083 1.0000
10.250 1.5244 0.01987 0.01313 -0.0853 0.2045 1.0000
10.500 1.5404 0.02048 0.01376 -0.0837 0.2009 1.0000
10.750 1.5552 0.02118 0.01447 -0.0820 0.1973 1.0000
11.000 1.5744 0.02157 0.01497 -0.0810 0.1932 1.0000
11.250 1.5904 0.02214 0.01556 -0.0795 0.1879 1.0000
11.500 1.6040 0.02290 0.01633 -0.0778 0.1829 1.0000
11.750 1.6222 0.02337 0.01691 -0.0767 0.1788 1.0000
12.000 1.6372 0.02405 0.01762 -0.0753 0.1747 1.0000
12.250 1.6481 0.02499 0.01856 -0.0733 0.1703 1.0000
12.500 1.6656 0.02552 0.01922 -0.0723 0.1663 1.0000
12.750 1.6801 0.02626 0.02001 -0.0709 0.1616 1.0000
13.000 1.6897 0.02733 0.02108 -0.0690 0.1568 1.0000
13.250 1.7060 0.02798 0.02185 -0.0680 0.1520 1.0000
13.500 1.7172 0.02899 0.02287 -0.0664 0.1460 1.0000
13.750 1.7286 0.03000 0.02396 -0.0650 0.1407 1.0000
14.000 1.7397 0.03107 0.02508 -0.0636 0.1345 1.0000
14.250 1.7482 0.03236 0.02641 -0.0620 0.1283 1.0000
14.500 1.7555 0.03379 0.02787 -0.0604 0.1201 1.0000
14.750 1.7608 0.03543 0.02953 -0.0588 0.1097 1.0000
15.000 1.7586 0.03779 0.03183 -0.0568 0.0952 1.0000
15.250 1.7461 0.04122 0.03515 -0.0544 0.0732 1.0000
15.500 1.7240 0.04581 0.03963 -0.0520 0.0522 1.0000
15.750 1.7022 0.05074 0.04453 -0.0503 0.0390 1.0000
16.000 1.6845 0.05557 0.04942 -0.0493 0.0316 1.0000
16.250 1.6684 0.06046 0.05439 -0.0489 0.0275 1.0000
16.500 1.6550 0.06524 0.05929 -0.0489 0.0248 1.0000
16.750 1.6392 0.07055 0.06472 -0.0493 0.0230 1.0000
17.000 1.6205 0.07648 0.07077 -0.0501 0.0216 1.0000
17.250 1.6067 0.08181 0.07626 -0.0510 0.0207 1.0000
17.500 1.5900 0.08774 0.08233 -0.0523 0.0199 1.0000
17.750 1.5716 0.09406 0.08879 -0.0540 0.0193 1.0000
18.000 1.5514 0.10075 0.09562 -0.0559 0.0189 1.0000
18.250 1.5304 0.10767 0.10269 -0.0580 0.0185 1.0000
18.500 1.5087 0.11487 0.11003 -0.0605 0.0182 1.0000
18.750 1.4870 0.12220 0.11749 -0.0633 0.0179 1.0000
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