USNPS4 (smoothed) (usnps4-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USNPS4 (smoothed) (usnps4-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.83 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usnps4-il-1000000.txt Download as CSV file: xf-usnps4-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0889 0.09531 0.09367 -0.0745 0.9806 0.0131
-9.750 -0.0825 0.09108 0.08945 -0.0768 0.9795 0.0139
-9.500 -0.1993 0.10282 0.10112 -0.0644 0.9871 0.0123
-9.250 -0.1859 0.09913 0.09743 -0.0679 0.9864 0.0126
-9.000 -0.1721 0.09528 0.09357 -0.0718 0.9857 0.0131
-8.500 -0.1608 0.08540 0.08371 -0.0809 0.9789 0.0142
-8.250 -0.1487 0.08061 0.07892 -0.0862 0.9770 0.0143
-8.000 -0.1355 0.07524 0.07356 -0.0931 0.9754 0.0143
-7.750 -0.1343 0.07056 0.06889 -0.0965 0.9690 0.0146
-7.500 -0.1140 0.06741 0.06572 -0.1008 0.9670 0.0148
-7.250 -0.0900 0.06373 0.06202 -0.1067 0.9656 0.0151
-7.000 -0.0629 0.05932 0.05757 -0.1140 0.9646 0.0156
-6.750 -0.0336 0.05396 0.05214 -0.1222 0.9636 0.0166
-6.500 -0.0172 0.04536 0.04331 -0.1282 0.9557 0.0176
-6.250 0.0017 0.03816 0.03589 -0.1328 0.9530 0.0180
-6.000 0.0303 0.03646 0.03413 -0.1352 0.9514 0.0183
-5.750 0.0211 0.01566 0.01160 -0.1335 0.9425 0.0171
-5.500 0.0527 0.01446 0.01011 -0.1344 0.9398 0.0176
-5.250 0.0840 0.01278 0.00822 -0.1356 0.9373 0.0185
-5.000 0.1080 0.01238 0.00776 -0.1347 0.9303 0.0190
-4.750 0.1388 0.01174 0.00702 -0.1354 0.9255 0.0196
-4.500 0.1679 0.01109 0.00627 -0.1356 0.9196 0.0202
-4.250 0.1967 0.01055 0.00561 -0.1357 0.9123 0.0208
-4.000 0.2262 0.01015 0.00513 -0.1360 0.9047 0.0213
-3.750 0.2552 0.00942 0.00430 -0.1363 0.8959 0.0224
-3.500 0.2834 0.00919 0.00404 -0.1363 0.8852 0.0232
-3.250 0.3121 0.00892 0.00372 -0.1364 0.8735 0.0240
-3.000 0.3404 0.00869 0.00340 -0.1364 0.8602 0.0249
-2.750 0.3681 0.00854 0.00316 -0.1362 0.8450 0.0257
-2.500 0.3947 0.00821 0.00274 -0.1359 0.8281 0.0272
-2.250 0.4212 0.00815 0.00261 -0.1355 0.8096 0.0287
-2.000 0.4473 0.00814 0.00250 -0.1350 0.7901 0.0305
-1.750 0.4728 0.00802 0.00228 -0.1345 0.7696 0.0327
-1.500 0.4980 0.00803 0.00222 -0.1338 0.7477 0.0353
-1.250 0.5229 0.00808 0.00215 -0.1331 0.7255 0.0379
-1.000 0.5478 0.00808 0.00207 -0.1324 0.7024 0.0425
-0.750 0.5722 0.00816 0.00204 -0.1316 0.6794 0.0464
-0.500 0.5969 0.00821 0.00202 -0.1309 0.6554 0.0523
-0.250 0.6212 0.00830 0.00200 -0.1302 0.6315 0.0586
0.000 0.6461 0.00839 0.00201 -0.1295 0.6081 0.0663
0.250 0.6704 0.00848 0.00203 -0.1288 0.5847 0.0810
0.500 0.6950 0.00846 0.00208 -0.1282 0.5607 0.1433
0.750 0.7126 0.00696 0.00237 -0.1269 0.5403 0.8470
1.000 0.7420 0.00694 0.00247 -0.1269 0.5182 1.0000
1.250 0.7658 0.00714 0.00253 -0.1260 0.4962 1.0000
1.500 0.7897 0.00735 0.00261 -0.1253 0.4754 1.0000
1.750 0.8142 0.00755 0.00268 -0.1246 0.4571 1.0000
2.000 0.8389 0.00775 0.00277 -0.1240 0.4394 1.0000
2.250 0.8635 0.00795 0.00287 -0.1234 0.4218 1.0000
2.500 0.8882 0.00816 0.00297 -0.1228 0.4052 1.0000
2.750 0.9129 0.00836 0.00308 -0.1223 0.3906 1.0000
3.000 0.9377 0.00856 0.00320 -0.1217 0.3769 1.0000
3.250 0.9622 0.00878 0.00333 -0.1212 0.3634 1.0000
3.500 0.9868 0.00899 0.00346 -0.1206 0.3501 1.0000
3.750 1.0116 0.00918 0.00359 -0.1201 0.3385 1.0000
4.000 1.0362 0.00938 0.00373 -0.1195 0.3281 1.0000
4.250 1.0602 0.00961 0.00389 -0.1189 0.3176 1.0000
4.500 1.0850 0.00979 0.00403 -0.1184 0.3084 1.0000
4.750 1.1089 0.01001 0.00420 -0.1177 0.2991 1.0000
5.000 1.1327 0.01024 0.00437 -0.1171 0.2896 1.0000
5.250 1.1567 0.01044 0.00454 -0.1164 0.2819 1.0000
5.500 1.1797 0.01068 0.00473 -0.1156 0.2739 1.0000
5.750 1.2027 0.01087 0.00491 -0.1148 0.2673 1.0000
6.000 1.2249 0.01111 0.00512 -0.1138 0.2601 1.0000
6.250 1.2474 0.01134 0.00533 -0.1129 0.2537 1.0000
6.500 1.2696 0.01158 0.00555 -0.1119 0.2470 1.0000
6.750 1.2912 0.01185 0.00580 -0.1109 0.2405 1.0000
7.000 1.3138 0.01207 0.00602 -0.1100 0.2353 1.0000
7.250 1.3352 0.01237 0.00628 -0.1090 0.2294 1.0000
7.500 1.3573 0.01262 0.00654 -0.1080 0.2247 1.0000
7.750 1.3793 0.01287 0.00680 -0.1071 0.2199 1.0000
8.000 1.3998 0.01320 0.00711 -0.1060 0.2146 1.0000
8.250 1.4213 0.01348 0.00740 -0.1050 0.2102 1.0000
8.500 1.4428 0.01375 0.00769 -0.1040 0.2059 1.0000
8.750 1.4630 0.01410 0.00803 -0.1029 0.2012 1.0000
9.000 1.4829 0.01445 0.00839 -0.1016 0.1971 1.0000
9.250 1.5042 0.01473 0.00871 -0.1007 0.1940 1.0000
9.500 1.5244 0.01507 0.00906 -0.0996 0.1904 1.0000
9.750 1.5431 0.01548 0.00948 -0.0982 0.1863 1.0000
10.000 1.5625 0.01586 0.00987 -0.0970 0.1823 1.0000
10.250 1.5826 0.01620 0.01023 -0.0960 0.1768 1.0000
10.500 1.5997 0.01670 0.01071 -0.0944 0.1710 1.0000
10.750 1.6192 0.01706 0.01112 -0.0933 0.1679 1.0000
11.000 1.6380 0.01746 0.01155 -0.0921 0.1639 1.0000
11.250 1.6549 0.01798 0.01207 -0.0906 0.1594 1.0000
11.500 1.6721 0.01848 0.01259 -0.0893 0.1552 1.0000
11.750 1.6901 0.01893 0.01308 -0.0880 0.1509 1.0000
12.000 1.7052 0.01955 0.01369 -0.0864 0.1453 1.0000
12.250 1.7217 0.02009 0.01427 -0.0850 0.1405 1.0000
12.500 1.7363 0.02075 0.01493 -0.0834 0.1344 1.0000
12.750 1.7505 0.02146 0.01565 -0.0817 0.1286 1.0000
13.000 1.7635 0.02223 0.01642 -0.0800 0.1217 1.0000
13.250 1.7756 0.02308 0.01728 -0.0781 0.1146 1.0000
13.500 1.7842 0.02416 0.01833 -0.0759 0.1051 1.0000
13.750 1.7896 0.02548 0.01960 -0.0734 0.0925 1.0000
14.000 1.7858 0.02749 0.02148 -0.0700 0.0738 1.0000
14.250 1.7736 0.03020 0.02406 -0.0659 0.0522 1.0000
14.500 1.7599 0.03324 0.02702 -0.0621 0.0357 1.0000
14.750 1.7513 0.03605 0.02982 -0.0593 0.0266 1.0000
15.000 1.7472 0.03864 0.03244 -0.0572 0.0216 1.0000
15.250 1.7454 0.04116 0.03502 -0.0555 0.0187 1.0000
15.500 1.7439 0.04376 0.03770 -0.0541 0.0166 1.0000
15.750 1.7414 0.04657 0.04058 -0.0530 0.0152 1.0000
16.000 1.7358 0.04984 0.04394 -0.0519 0.0138 1.0000
16.250 1.7349 0.05273 0.04693 -0.0513 0.0131 1.0000
16.500 1.7307 0.05609 0.05039 -0.0509 0.0124 1.0000
16.750 1.7231 0.05998 0.05437 -0.0506 0.0117 1.0000
17.000 1.7115 0.06452 0.05902 -0.0506 0.0111 1.0000
17.250 1.7030 0.06880 0.06341 -0.0509 0.0107 1.0000
17.500 1.6940 0.07326 0.06800 -0.0514 0.0104 1.0000
17.750 1.6831 0.07808 0.07294 -0.0521 0.0100 1.0000
18.000 1.6690 0.08341 0.07840 -0.0531 0.0097 1.0000
18.250 1.6528 0.08920 0.08431 -0.0543 0.0095 1.0000
18.500 1.6347 0.09541 0.09064 -0.0559 0.0093 1.0000
18.750 1.6151 0.10190 0.09726 -0.0577 0.0092 1.0000
19.000 1.5941 0.10870 0.10420 -0.0598 0.0090 1.0000
19.250 1.5730 0.11567 0.11130 -0.0621 0.0089 1.0000
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