GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 50,000 Max Cl/Cd: 20.69 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe318-il-50000.txt Download as CSV file: xf-goe318-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4357 0.12164 0.11548 0.0118 1.0000 0.1431
-9.000 -0.4409 0.12056 0.11449 0.0078 1.0000 0.1473
-8.750 -0.4313 0.11581 0.10979 0.0069 1.0000 0.1505
-8.500 -0.4171 0.11147 0.10547 0.0070 1.0000 0.1574
-8.250 -0.4229 0.11025 0.10437 0.0024 1.0000 0.1627
-8.000 -0.4080 0.10499 0.09916 0.0026 1.0000 0.1675
-7.750 -0.4022 0.10212 0.09636 0.0006 1.0000 0.1762
-7.500 -0.3983 0.09870 0.09306 -0.0020 1.0000 0.1818
-7.250 -0.3915 0.09594 0.09037 -0.0052 1.0000 0.1928
-6.500 -0.3658 0.08658 0.08122 -0.0177 1.0000 0.2251
-6.250 -0.3487 0.08180 0.07652 -0.0139 1.0000 0.2371
-6.000 -0.3422 0.07880 0.07361 -0.0145 1.0000 0.2483
-5.500 -0.3669 0.07644 0.07143 -0.0106 1.0000 0.2634
-5.250 -0.3800 0.07532 0.07036 -0.0103 1.0000 0.2737
-5.000 -0.3861 0.07377 0.06883 -0.0094 1.0000 0.2881
-4.500 0.0375 0.04273 0.03718 -0.0172 1.0000 1.0000
-4.250 0.0550 0.04080 0.03531 -0.0209 1.0000 1.0000
-4.000 0.0692 0.03926 0.03382 -0.0239 1.0000 1.0000
-3.750 0.0763 0.03833 0.03295 -0.0254 1.0000 1.0000
-3.500 0.0111 0.04168 0.03649 -0.0112 1.0000 0.9757
-3.250 -0.0684 0.04516 0.04018 0.0053 1.0000 0.9433
-3.000 -0.1131 0.04599 0.04112 0.0112 0.9834 0.8852
-2.750 -0.1597 0.04639 0.04165 0.0157 0.9646 0.8337
-2.500 -0.0264 0.04113 0.03348 -0.0675 0.9331 0.2399
-2.250 0.0383 0.03821 0.02967 -0.0743 0.9254 0.1931
-2.000 0.0750 0.03642 0.02757 -0.0765 0.9152 0.1847
-1.750 0.1209 0.03498 0.02559 -0.0797 0.9061 0.1739
-1.500 0.1679 0.03363 0.02377 -0.0828 0.8968 0.1673
-1.250 0.2008 0.03303 0.02278 -0.0836 0.8859 0.1652
-1.000 0.2371 0.03233 0.02197 -0.0851 0.8757 0.1703
-0.750 0.2784 0.03179 0.02116 -0.0867 0.8657 0.1772
-0.500 0.3079 0.03153 0.02079 -0.0868 0.8538 0.1824
-0.250 0.3382 0.03138 0.02055 -0.0869 0.8419 0.1922
0.000 0.3687 0.03112 0.02035 -0.0869 0.8297 0.2124
0.250 0.3988 0.03059 0.02010 -0.0866 0.8163 0.2623
0.500 0.4358 0.02846 0.01938 -0.0856 0.8027 1.0000
0.750 0.4602 0.02906 0.01962 -0.0843 0.7865 1.0000
1.000 0.4839 0.02964 0.01995 -0.0829 0.7704 1.0000
1.250 0.5075 0.03022 0.02034 -0.0815 0.7548 1.0000
1.500 0.5311 0.03081 0.02076 -0.0802 0.7398 1.0000
1.750 0.5546 0.03140 0.02122 -0.0788 0.7252 1.0000
2.000 0.5781 0.03196 0.02167 -0.0774 0.7107 1.0000
2.250 0.6018 0.03247 0.02208 -0.0759 0.6963 1.0000
2.500 0.6261 0.03286 0.02237 -0.0742 0.6824 1.0000
2.750 0.6488 0.03344 0.02289 -0.0728 0.6672 1.0000
3.000 0.6715 0.03399 0.02340 -0.0713 0.6518 1.0000
3.250 0.6943 0.03454 0.02390 -0.0699 0.6365 1.0000
3.500 0.7170 0.03516 0.02449 -0.0686 0.6212 1.0000
3.750 0.7392 0.03594 0.02526 -0.0675 0.6062 1.0000
4.000 0.7611 0.03681 0.02615 -0.0666 0.5913 1.0000
4.250 0.7824 0.03781 0.02717 -0.0658 0.5767 1.0000
4.500 0.8028 0.03902 0.02840 -0.0652 0.5627 1.0000
4.750 0.8218 0.04055 0.02998 -0.0649 0.5494 1.0000
5.000 0.8398 0.04236 0.03186 -0.0649 0.5379 1.0000
5.250 0.8658 0.04289 0.03242 -0.0638 0.5307 1.0000
5.500 0.8717 0.04691 0.03656 -0.0656 0.5191 1.0000
5.750 0.9022 0.04685 0.03652 -0.0640 0.5145 1.0000
6.000 0.8914 0.05329 0.04310 -0.0673 0.5034 1.0000
6.250 0.9030 0.05620 0.04610 -0.0678 0.4976 1.0000
6.500 0.8720 0.06459 0.05452 -0.0719 0.4931 1.0000
6.750 0.8566 0.07015 0.06008 -0.0733 0.4929 1.0000
7.000 0.8472 0.07512 0.06507 -0.0746 0.4942 1.0000
7.250 0.8438 0.07951 0.06950 -0.0756 0.4960 1.0000
7.500 0.8505 0.08336 0.07342 -0.0766 0.4985 1.0000
7.750 0.7301 0.09856 0.08857 -0.0869 0.6257 1.0000
8.000 0.7612 0.10258 0.09269 -0.0887 0.6209 1.0000
8.250 0.7465 0.10386 0.09398 -0.0867 0.6126 1.0000
8.500 0.7719 0.10746 0.09770 -0.0879 0.6064 1.0000
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Polar data table (+)
Polar graphs
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