USA 35 AIRFOIL (usa35-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 35 AIRFOIL (usa35-il) Reynolds number: 100,000 Max Cl/Cd: 35.44 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa35-il-100000.txt Download as CSV file: xf-usa35-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: USA 35 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 0.0650 0.10212 0.09716 -0.0974 0.9220 0.1273
-8.500 0.0512 0.10035 0.09540 -0.1040 0.9089 0.1330
-8.250 0.0767 0.09564 0.09069 -0.1052 0.9015 0.1347
-8.000 0.1046 0.09227 0.08730 -0.1053 0.8933 0.1375
-7.750 0.1154 0.08968 0.08470 -0.1063 0.8816 0.1420
-7.500 0.0731 0.08837 0.08342 -0.1118 0.8625 0.1467
-7.250 0.1214 0.08399 0.07899 -0.1091 0.8590 0.1491
-7.000 0.1337 0.08199 0.07698 -0.1078 0.8455 0.1526
-6.500 0.1172 0.07726 0.07223 -0.1116 0.8210 0.1626
-6.250 0.1410 0.07524 0.07018 -0.1084 0.8118 0.1666
-6.000 0.1187 0.07231 0.06714 -0.1184 0.7992 0.1774
-5.750 0.1420 0.07018 0.06506 -0.1132 0.7906 0.1797
-5.500 0.1583 0.06842 0.06330 -0.1113 0.7814 0.1843
-5.250 0.1606 0.06481 0.05951 -0.1183 0.7751 0.1963
-5.000 0.1709 0.06355 0.05834 -0.1149 0.7637 0.1991
-4.750 0.1792 0.06077 0.05533 -0.1206 0.7567 0.2147
-4.500 0.1953 0.05884 0.05347 -0.1176 0.7492 0.2176
-4.250 0.2093 0.05742 0.05206 -0.1162 0.7409 0.2240
-4.000 0.2249 0.04176 0.03476 -0.1324 0.7362 0.1351
-3.750 0.2499 0.03892 0.03160 -0.1328 0.7310 0.1283
-3.500 0.2642 0.03602 0.02774 -0.1318 0.7220 0.1215
-3.250 0.2925 0.03447 0.02621 -0.1321 0.7166 0.1241
-3.000 0.3259 0.03300 0.02448 -0.1328 0.7125 0.1268
-2.750 0.3399 0.03259 0.02391 -0.1310 0.7031 0.1281
-2.500 0.3694 0.03137 0.02236 -0.1309 0.6969 0.1305
-2.250 0.4047 0.03003 0.02068 -0.1316 0.6925 0.1350
-2.000 0.4218 0.02995 0.02066 -0.1301 0.6842 0.1384
-1.750 0.4486 0.02940 0.01997 -0.1296 0.6776 0.1432
-1.500 0.4826 0.02846 0.01889 -0.1301 0.6731 0.1496
-1.250 0.5070 0.02829 0.01870 -0.1295 0.6671 0.1559
-1.000 0.5267 0.02829 0.01870 -0.1282 0.6596 0.1627
-0.750 0.5579 0.02774 0.01816 -0.1283 0.6545 0.1728
-0.500 0.5933 0.02701 0.01742 -0.1290 0.6507 0.1866
-0.250 0.6050 0.02754 0.01811 -0.1268 0.6424 0.1983
0.000 0.6313 0.02721 0.01791 -0.1263 0.6363 0.2219
0.250 0.6648 0.02621 0.01723 -0.1267 0.6320 0.2945
0.500 0.6775 0.02507 0.01767 -0.1237 0.6264 0.6624
0.750 0.7101 0.02506 0.01807 -0.1236 0.6187 1.0000
1.000 0.7422 0.02505 0.01776 -0.1239 0.6135 1.0000
1.250 0.7808 0.02488 0.01725 -0.1251 0.6095 1.0000
1.500 0.7844 0.02610 0.01852 -0.1218 0.6001 1.0000
1.750 0.8145 0.02617 0.01839 -0.1219 0.5943 1.0000
2.000 0.8530 0.02599 0.01794 -0.1231 0.5900 1.0000
2.250 0.8588 0.02723 0.01924 -0.1202 0.5814 1.0000
2.500 0.8850 0.02752 0.01941 -0.1198 0.5750 1.0000
2.750 0.9234 0.02733 0.01899 -0.1210 0.5705 1.0000
3.000 0.9321 0.02849 0.02018 -0.1185 0.5622 1.0000
3.250 0.9556 0.02889 0.02050 -0.1177 0.5553 1.0000
3.500 0.9941 0.02871 0.02010 -0.1190 0.5506 1.0000
3.750 1.0040 0.02991 0.02134 -0.1166 0.5431 1.0000
4.000 1.0205 0.03071 0.02212 -0.1151 0.5359 1.0000
4.250 1.0571 0.03063 0.02189 -0.1161 0.5312 1.0000
4.500 1.0797 0.03133 0.02252 -0.1155 0.5255 1.0000
4.750 1.0797 0.03286 0.02416 -0.1119 0.5169 1.0000
5.000 1.1141 0.03285 0.02401 -0.1126 0.5120 1.0000
5.250 1.1576 0.03266 0.02363 -0.1147 0.5084 1.0000
5.500 1.1266 0.03579 0.02705 -0.1075 0.4989 1.0000
5.750 1.1504 0.03630 0.02752 -0.1070 0.4937 1.0000
6.000 1.1949 0.03587 0.02694 -0.1090 0.4902 1.0000
6.250 1.1729 0.03876 0.03000 -0.1032 0.4826 1.0000
6.500 1.1481 0.04166 0.03302 -0.0972 0.4751 1.0000
6.750 1.2015 0.04058 0.03181 -0.1000 0.4720 1.0000
7.000 1.2750 0.03859 0.02958 -0.1052 0.4691 1.0000
7.250 1.0831 0.05301 0.04458 -0.0858 0.4522 1.0000
7.500 1.1928 0.04600 0.03734 -0.0903 0.4528 1.0000
7.750 1.3057 0.04092 0.03196 -0.0984 0.4508 1.0000
8.000 1.0907 0.05957 0.05116 -0.0815 0.4321 1.0000
8.250 1.1696 0.05399 0.04545 -0.0827 0.4325 1.0000
8.500 1.2577 0.04885 0.04015 -0.0857 0.4324 1.0000
8.750 1.3578 0.04435 0.03542 -0.0917 0.4311 1.0000
9.000 0.8717 0.10094 0.09298 -0.0807 0.3812 1.0000
9.250 0.9136 0.09879 0.09078 -0.0796 0.3793 1.0000
9.500 0.8671 0.10818 0.10027 -0.0805 0.3660 1.0000
9.750 0.9029 0.10673 0.09878 -0.0794 0.3633 1.0000
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Polar data table (+)
Polar graphs
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