GM15 (smoothed) (gm15sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GM15 (smoothed) (gm15sm-il) Reynolds number: 50,000 Max Cl/Cd: 45.24 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-gm15sm-il-50000.txt Download as CSV file: xf-gm15sm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GM15 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3586 0.10565 0.09918 -0.0227 1.0000 0.1709
-7.000 -0.3364 0.09951 0.09301 -0.0210 1.0000 0.1799
-6.750 -0.3508 0.09956 0.09323 -0.0203 1.0000 0.1841
-6.500 -0.3432 0.09557 0.08930 -0.0185 1.0000 0.1898
-6.250 -0.3474 0.09429 0.08812 -0.0182 1.0000 0.1972
-6.000 -0.3473 0.09160 0.08553 -0.0176 1.0000 0.2017
-5.750 -0.3444 0.08918 0.08317 -0.0165 1.0000 0.2100
-5.500 -0.3455 0.08713 0.08122 -0.0176 1.0000 0.2150
-5.250 -0.3399 0.08421 0.07830 -0.0157 1.0000 0.2229
-5.000 -0.3374 0.08179 0.07596 -0.0169 1.0000 0.2299
-4.750 -0.3299 0.08033 0.07454 -0.0217 1.0000 0.2415
-4.500 -0.3253 0.07628 0.07055 -0.0164 1.0000 0.2469
-4.250 -0.3161 0.07369 0.06800 -0.0188 1.0000 0.2578
-4.000 -0.3034 0.07109 0.06541 -0.0215 1.0000 0.2706
-3.750 -0.2891 0.06826 0.06259 -0.0236 1.0000 0.2842
-3.500 -0.2820 0.06502 0.05940 -0.0206 1.0000 0.2919
-3.250 -0.2604 0.06221 0.05656 -0.0253 1.0000 0.3127
-3.000 -0.1408 0.04892 0.04231 -0.0626 1.0000 0.1849
-2.750 -0.1480 0.04933 0.04303 -0.0540 1.0000 0.2231
-2.500 -0.0045 0.03145 0.02258 -0.0878 1.0000 0.1297
-2.250 0.0238 0.02962 0.02052 -0.0885 1.0000 0.1416
-2.000 0.0561 0.02757 0.01800 -0.0898 1.0000 0.1564
-1.750 0.0828 0.02627 0.01661 -0.0897 1.0000 0.1783
-1.500 0.1078 0.02550 0.01581 -0.0893 1.0000 0.2218
-1.250 0.1292 0.02520 0.01566 -0.0880 1.0000 0.2929
-1.000 0.1489 0.02508 0.01562 -0.0866 1.0000 0.3681
-0.750 0.1694 0.02484 0.01534 -0.0855 1.0000 0.4246
-0.500 0.1912 0.02459 0.01502 -0.0849 1.0000 0.4710
-0.250 0.2143 0.02441 0.01472 -0.0847 1.0000 0.5140
0.000 0.2377 0.02429 0.01455 -0.0847 1.0000 0.5574
0.250 0.2614 0.02420 0.01449 -0.0849 1.0000 0.6062
0.500 0.2856 0.02397 0.01451 -0.0851 1.0000 0.6750
0.750 0.2965 0.02345 0.01457 -0.0837 1.0000 1.0000
1.000 0.3228 0.02440 0.01502 -0.0857 1.0000 1.0000
1.250 0.3430 0.02538 0.01569 -0.0862 1.0000 1.0000
1.500 0.3868 0.02667 0.01668 -0.0912 0.9881 1.0000
1.750 0.4384 0.02786 0.01764 -0.0971 0.9706 1.0000
2.000 0.4874 0.02893 0.01857 -0.1022 0.9528 1.0000
2.250 0.5387 0.02992 0.01949 -0.1074 0.9356 1.0000
2.500 0.5794 0.03075 0.02029 -0.1106 0.9163 1.0000
2.750 0.6229 0.03146 0.02100 -0.1139 0.8975 1.0000
3.000 0.6716 0.03197 0.02157 -0.1178 0.8801 1.0000
3.250 0.7052 0.03255 0.02226 -0.1191 0.8598 1.0000
3.500 0.7498 0.03281 0.02263 -0.1218 0.8413 1.0000
3.750 0.7978 0.03280 0.02279 -0.1245 0.8238 1.0000
4.000 0.8316 0.03307 0.02327 -0.1251 0.8029 1.0000
4.250 0.8833 0.03257 0.02302 -0.1276 0.7853 1.0000
4.500 0.9231 0.03234 0.02301 -0.1282 0.7656 1.0000
4.750 0.9640 0.03193 0.02284 -0.1286 0.7456 1.0000
5.000 1.0105 0.03110 0.02238 -0.1292 0.7264 1.0000
5.250 1.0435 0.03099 0.02253 -0.1284 0.7034 1.0000
5.500 1.0778 0.03081 0.02261 -0.1275 0.6801 1.0000
5.750 1.1157 0.03038 0.02246 -0.1266 0.6562 1.0000
6.000 1.1486 0.03023 0.02264 -0.1251 0.6297 1.0000
6.250 1.1744 0.02886 0.02135 -0.1205 0.5834 1.0000
6.500 1.1909 0.02678 0.01900 -0.1137 0.5171 1.0000
6.750 1.1983 0.02649 0.01874 -0.1082 0.4575 1.0000
7.000 1.1915 0.02692 0.01875 -0.1006 0.3502 1.0000
7.250 1.1752 0.03059 0.02078 -0.0936 0.1909 1.0000
7.500 1.1808 0.03381 0.02332 -0.0904 0.1397 1.0000
7.750 1.1999 0.03671 0.02591 -0.0885 0.1178 1.0000
8.000 1.2317 0.03973 0.02895 -0.0879 0.1027 1.0000
8.250 1.2648 0.04318 0.03231 -0.0880 0.0913 1.0000
8.500 1.2936 0.04670 0.03641 -0.0870 0.0879 1.0000
8.750 1.3166 0.05071 0.04094 -0.0855 0.0862 1.0000
9.000 1.3323 0.05498 0.04576 -0.0835 0.0856 1.0000
9.250 1.3411 0.05916 0.05045 -0.0812 0.0843 1.0000
9.500 1.3465 0.06327 0.05497 -0.0788 0.0826 1.0000
9.750 1.3488 0.06760 0.05966 -0.0765 0.0815 1.0000
10.000 1.3381 0.07216 0.06476 -0.0734 0.0823 1.0000
10.250 1.3207 0.07689 0.06995 -0.0704 0.0839 1.0000
10.500 1.2994 0.08143 0.07481 -0.0676 0.0853 1.0000
10.750 1.2748 0.08588 0.07950 -0.0653 0.0866 1.0000
11.000 1.2505 0.09087 0.08467 -0.0645 0.0878 1.0000
11.250 1.2285 0.09651 0.09045 -0.0650 0.0891 1.0000
11.500 1.2108 0.10267 0.09671 -0.0664 0.0903 1.0000
11.750 1.2060 0.10906 0.10314 -0.0675 0.0914 1.0000
12.000 1.1308 0.12476 0.11898 -0.0817 0.1033 1.0000
12.250 1.0856 0.14217 0.13625 -0.0962 0.1137 1.0000
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Polar data table (+)
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