FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il) Reynolds number: 100,000 Max Cl/Cd: 64.54 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63137sm-il-100000-n5.txt Download as CSV file: xf-fx63137sm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-137 13.7% 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 -0.1402 0.09392 0.08894 -0.0803 0.9456 0.0378
-8.500 -0.1262 0.09014 0.08516 -0.0834 0.9399 0.0368
-8.250 -0.1173 0.08592 0.08096 -0.0867 0.9325 0.0358
-7.750 -0.1231 0.07183 0.06688 -0.0985 0.9143 0.0326
-7.500 -0.1175 0.06564 0.06067 -0.1046 0.9077 0.0323
-7.250 -0.1222 0.05797 0.05294 -0.1125 0.8952 0.0318
-7.000 -0.1188 0.04746 0.04203 -0.1305 0.8830 0.0314
-6.750 -0.0870 0.03901 0.03269 -0.1457 0.8769 0.0322
-6.500 -0.0436 0.03461 0.02770 -0.1540 0.8743 0.0335
-6.250 -0.0192 0.03260 0.02543 -0.1557 0.8661 0.0342
-6.000 0.0210 0.02995 0.02236 -0.1602 0.8622 0.0351
-5.750 0.0634 0.02764 0.01963 -0.1643 0.8593 0.0362
-5.500 0.1018 0.02584 0.01745 -0.1671 0.8554 0.0378
-5.250 0.1302 0.02483 0.01634 -0.1678 0.8483 0.0399
-5.000 0.1673 0.02376 0.01516 -0.1700 0.8440 0.0428
-4.750 0.2070 0.02259 0.01379 -0.1722 0.8408 0.0452
-4.500 0.2339 0.02192 0.01318 -0.1725 0.8334 0.0477
-4.250 0.2688 0.02124 0.01241 -0.1741 0.8280 0.0531
-4.000 0.3096 0.02044 0.01159 -0.1769 0.8242 0.0597
-3.750 0.3422 0.01992 0.01106 -0.1783 0.8176 0.0695
-3.500 0.3798 0.01924 0.01041 -0.1808 0.8117 0.0885
-3.250 0.4254 0.01825 0.00964 -0.1851 0.8075 0.1507
-3.000 0.4656 0.01742 0.00949 -0.1888 0.8016 0.3206
-2.750 0.4968 0.01744 0.00965 -0.1894 0.7948 0.4077
-2.500 0.5318 0.01750 0.00964 -0.1905 0.7898 0.4560
-2.250 0.5580 0.01769 0.00981 -0.1899 0.7824 0.4816
-2.000 0.5878 0.01781 0.00984 -0.1900 0.7759 0.5055
-1.750 0.6211 0.01788 0.00980 -0.1906 0.7710 0.5293
-1.500 0.6443 0.01811 0.01001 -0.1896 0.7627 0.5464
-1.250 0.6747 0.01812 0.00995 -0.1898 0.7567 0.5585
-1.000 0.7029 0.01819 0.00996 -0.1897 0.7500 0.5689
-0.750 0.7316 0.01827 0.00995 -0.1899 0.7428 0.5801
-0.500 0.7632 0.01823 0.00984 -0.1902 0.7375 0.5890
-0.250 0.7886 0.01840 0.00997 -0.1899 0.7292 0.5995
0.000 0.8178 0.01842 0.00995 -0.1899 0.7228 0.6083
0.250 0.8462 0.01851 0.01000 -0.1900 0.7159 0.6184
0.500 0.8729 0.01861 0.01009 -0.1896 0.7083 0.6276
0.750 0.9045 0.01861 0.01002 -0.1901 0.7026 0.6376
1.000 0.9284 0.01881 0.01025 -0.1894 0.6938 0.6475
1.250 0.9584 0.01883 0.01023 -0.1896 0.6874 0.6573
1.500 0.9840 0.01902 0.01043 -0.1893 0.6791 0.6684
1.750 1.0115 0.01908 0.01049 -0.1890 0.6719 0.6778
2.000 1.0376 0.01924 0.01066 -0.1886 0.6640 0.6888
2.250 1.0645 0.01935 0.01077 -0.1883 0.6561 0.6999
2.500 1.0902 0.01949 0.01093 -0.1878 0.6483 0.7107
2.750 1.1161 0.01963 0.01109 -0.1873 0.6398 0.7227
3.000 1.1422 0.01977 0.01125 -0.1869 0.6318 0.7351
3.250 1.1663 0.01992 0.01144 -0.1860 0.6230 0.7471
3.500 1.1913 0.02007 0.01162 -0.1854 0.6146 0.7601
3.750 1.2157 0.02023 0.01182 -0.1846 0.6056 0.7740
4.000 1.2392 0.02042 0.01206 -0.1838 0.5966 0.7889
4.250 1.2634 0.02055 0.01221 -0.1829 0.5877 0.8046
4.500 1.2843 0.02076 0.01251 -0.1816 0.5780 0.8215
4.750 1.3078 0.02084 0.01261 -0.1805 0.5695 0.8407
5.000 1.3255 0.02107 0.01295 -0.1786 0.5590 0.8636
5.250 1.3445 0.02112 0.01304 -0.1767 0.5503 0.8961
5.500 1.3613 0.02124 0.01327 -0.1746 0.5398 1.0000
5.750 1.3880 0.02163 0.01365 -0.1747 0.5292 1.0000
6.000 1.4159 0.02194 0.01391 -0.1749 0.5190 1.0000
6.250 1.4379 0.02240 0.01443 -0.1741 0.5064 1.0000
6.500 1.4590 0.02282 0.01484 -0.1731 0.4917 1.0000
6.750 1.4777 0.02325 0.01522 -0.1716 0.4743 1.0000
7.000 1.4944 0.02375 0.01566 -0.1698 0.4562 1.0000
7.250 1.5096 0.02432 0.01620 -0.1678 0.4388 1.0000
7.500 1.5239 0.02494 0.01682 -0.1656 0.4237 1.0000
7.750 1.5378 0.02563 0.01751 -0.1635 0.4091 1.0000
8.000 1.5509 0.02637 0.01826 -0.1614 0.3947 1.0000
8.250 1.5627 0.02720 0.01909 -0.1591 0.3801 1.0000
8.500 1.5733 0.02811 0.02001 -0.1567 0.3652 1.0000
8.750 1.5827 0.02913 0.02102 -0.1543 0.3503 1.0000
9.000 1.5909 0.03026 0.02215 -0.1518 0.3351 1.0000
9.250 1.5978 0.03152 0.02342 -0.1494 0.3196 1.0000
9.500 1.6035 0.03292 0.02482 -0.1469 0.3039 1.0000
9.750 1.6082 0.03447 0.02638 -0.1445 0.2881 1.0000
10.000 1.6118 0.03618 0.02809 -0.1423 0.2722 1.0000
10.250 1.6144 0.03806 0.02999 -0.1401 0.2563 1.0000
10.500 1.6158 0.04014 0.03207 -0.1380 0.2402 1.0000
10.750 1.6162 0.04243 0.03434 -0.1360 0.2242 1.0000
11.000 1.6156 0.04491 0.03682 -0.1342 0.2088 1.0000
11.250 1.6141 0.04758 0.03949 -0.1325 0.1942 1.0000
11.500 1.6121 0.05044 0.04234 -0.1310 0.1812 1.0000
11.750 1.6105 0.05336 0.04528 -0.1297 0.1693 1.0000
12.000 1.6097 0.05632 0.04829 -0.1287 0.1592 1.0000
12.250 1.6076 0.05951 0.05150 -0.1277 0.1509 1.0000
12.500 1.6072 0.06262 0.05466 -0.1269 0.1432 1.0000
12.750 1.6060 0.06589 0.05795 -0.1262 0.1373 1.0000
13.000 1.6073 0.06897 0.06113 -0.1257 0.1313 1.0000
13.250 1.6062 0.07236 0.06454 -0.1253 0.1267 1.0000
13.500 1.6090 0.07534 0.06761 -0.1249 0.1225 1.0000
13.750 1.6123 0.07830 0.07070 -0.1247 0.1185 1.0000
14.000 1.6146 0.08140 0.07385 -0.1245 0.1151 1.0000
14.250 1.6178 0.08433 0.07675 -0.1242 0.1121 1.0000
14.500 1.6235 0.08707 0.07967 -0.1241 0.1090 1.0000
14.750 1.6282 0.08995 0.08268 -0.1241 0.1059 1.0000
15.000 1.6327 0.09283 0.08566 -0.1242 0.1033 1.0000
15.250 1.6390 0.09539 0.08825 -0.1241 0.1009 1.0000
15.500 1.6479 0.09755 0.09045 -0.1239 0.0988 1.0000
15.750 1.6529 0.10047 0.09358 -0.1241 0.0967 1.0000
16.000 1.6579 0.10337 0.09665 -0.1244 0.0945 1.0000
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Polar data table (+)
Polar graphs
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