GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 50,000 Max Cl/Cd: 23.44 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe316-il-50000.txt Download as CSV file: xf-goe316-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3961 0.10356 0.09722 -0.0085 1.0000 0.1532
-7.750 -0.3960 0.10042 0.09418 -0.0111 1.0000 0.1566
-7.500 -0.3825 0.09640 0.09018 -0.0099 1.0000 0.1657
-7.250 -0.3863 0.09422 0.08811 -0.0168 1.0000 0.1710
-7.000 -0.3731 0.09023 0.08416 -0.0147 1.0000 0.1830
-6.750 -0.3636 0.08648 0.08048 -0.0144 1.0000 0.1937
-6.500 -0.3577 0.08327 0.07735 -0.0161 1.0000 0.2063
-6.250 -0.3512 0.08018 0.07433 -0.0173 1.0000 0.2212
-6.000 -0.3438 0.07713 0.07134 -0.0173 1.0000 0.2378
-5.750 -0.3371 0.07428 0.06859 -0.0167 1.0000 0.2569
-5.500 -0.3381 0.07233 0.06672 -0.0187 1.0000 0.2805
-5.250 -0.3325 0.06929 0.06382 -0.0135 1.0000 0.3017
-5.000 -0.3383 0.06758 0.06223 -0.0114 1.0000 0.3290
-4.750 0.0163 0.04489 0.03866 -0.0126 1.0000 1.0000
-4.500 0.0304 0.04277 0.03660 -0.0144 1.0000 1.0000
-4.250 0.0447 0.04074 0.03464 -0.0162 1.0000 1.0000
-4.000 0.0590 0.03879 0.03277 -0.0180 1.0000 1.0000
-3.750 0.0731 0.03695 0.03103 -0.0199 1.0000 1.0000
-3.500 0.0320 0.03834 0.03264 -0.0095 1.0000 0.9725
-3.250 -0.0227 0.04001 0.03461 0.0021 1.0000 0.9293
-3.000 -0.0742 0.04136 0.03622 0.0121 1.0000 0.9032
-2.750 -0.1263 0.04260 0.03769 0.0224 1.0000 0.8942
-2.500 -0.1731 0.04314 0.03842 0.0311 1.0000 0.8804
-2.250 -0.2202 0.04337 0.03883 0.0395 1.0000 0.8674
-2.000 -0.0095 0.03655 0.02883 -0.0585 0.9539 0.2762
-1.750 0.0632 0.03479 0.02598 -0.0659 0.9373 0.2157
-1.500 0.1230 0.03299 0.02369 -0.0711 0.9206 0.1986
-1.250 0.1829 0.03153 0.02172 -0.0758 0.9037 0.1834
-1.000 0.2355 0.03010 0.01997 -0.0791 0.8856 0.1748
-0.750 0.2838 0.02923 0.01871 -0.0810 0.8670 0.1705
-0.500 0.3257 0.02805 0.01744 -0.0819 0.8479 0.1748
-0.250 0.3590 0.02745 0.01672 -0.0813 0.8250 0.1776
0.000 0.3916 0.02685 0.01598 -0.0801 0.8043 0.1803
0.250 0.4180 0.02661 0.01561 -0.0784 0.7815 0.1848
0.500 0.4435 0.02626 0.01526 -0.0768 0.7599 0.1961
1.000 0.4928 0.02547 0.01509 -0.0742 0.7190 0.3076
1.250 0.5223 0.02436 0.01511 -0.0725 0.7002 1.0000
1.500 0.5476 0.02493 0.01522 -0.0710 0.6833 1.0000
1.750 0.5724 0.02559 0.01554 -0.0701 0.6682 1.0000
2.000 0.5971 0.02635 0.01607 -0.0696 0.6546 1.0000
2.250 0.6219 0.02707 0.01661 -0.0690 0.6428 1.0000
2.500 0.6477 0.02763 0.01698 -0.0683 0.6328 1.0000
2.750 0.6709 0.02875 0.01805 -0.0684 0.6212 1.0000
3.000 0.6950 0.02978 0.01900 -0.0684 0.6123 1.0000
3.250 0.7193 0.03082 0.02001 -0.0684 0.6045 1.0000
3.500 0.7417 0.03224 0.02143 -0.0687 0.5970 1.0000
3.750 0.7646 0.03348 0.02267 -0.0688 0.5898 1.0000
4.000 0.7865 0.03494 0.02417 -0.0690 0.5832 1.0000
4.250 0.8050 0.03697 0.02627 -0.0696 0.5765 1.0000
4.500 0.8294 0.03812 0.02742 -0.0695 0.5722 1.0000
4.750 0.8384 0.04155 0.03100 -0.0709 0.5659 1.0000
5.000 0.8534 0.04396 0.03348 -0.0715 0.5603 1.0000
5.250 0.8788 0.04504 0.03461 -0.0711 0.5565 1.0000
5.500 0.8671 0.05094 0.04066 -0.0735 0.5515 1.0000
5.750 0.8633 0.05544 0.04523 -0.0748 0.5470 1.0000
6.000 0.8874 0.05675 0.04660 -0.0743 0.5421 1.0000
6.250 0.8741 0.06204 0.05193 -0.0756 0.5381 1.0000
6.500 0.8531 0.06731 0.05721 -0.0760 0.5357 1.0000
6.750 0.8468 0.07129 0.06122 -0.0762 0.5325 1.0000
7.000 0.8755 0.07251 0.06255 -0.0756 0.5239 1.0000
7.250 0.8604 0.07734 0.06740 -0.0762 0.5224 1.0000
7.500 0.8528 0.08169 0.07180 -0.0767 0.5218 1.0000
7.750 0.8485 0.08594 0.07611 -0.0774 0.5220 1.0000
8.000 0.8523 0.09034 0.08064 -0.0788 0.5264 1.0000
8.250 0.7614 0.10233 0.09259 -0.0861 0.6293 1.0000
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Polar data table (+)
Polar graphs
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