GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il) Reynolds number: 50,000 Max Cl/Cd: 39.83 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe137-il-50000-n5.txt Download as CSV file: xf-goe137-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 137 (MVA H.15) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3418 0.10836 0.10175 -0.0230 1.0000 0.0997
-8.250 -0.3500 0.10743 0.10096 -0.0262 1.0000 0.1018
-8.000 -0.3571 0.10618 0.09986 -0.0302 1.0000 0.1024
-7.750 -0.3351 0.09938 0.09304 -0.0257 1.0000 0.1058
-7.500 -0.3305 0.09636 0.09008 -0.0256 1.0000 0.1087
-7.250 -0.3292 0.09372 0.08754 -0.0265 1.0000 0.1118
-7.000 -0.3323 0.09179 0.08573 -0.0299 1.0000 0.1157
-6.750 -0.3360 0.09023 0.08425 -0.0357 1.0000 0.1172
-6.500 -0.3318 0.08631 0.08044 -0.0349 1.0000 0.1181
-6.250 -0.3255 0.08266 0.07686 -0.0305 1.0000 0.1216
-6.000 -0.3232 0.08013 0.07439 -0.0302 1.0000 0.1261
-5.750 -0.3219 0.07846 0.07268 -0.0367 1.0000 0.1320
-5.500 -0.3189 0.07505 0.06935 -0.0358 1.0000 0.1332
-5.250 -0.2990 0.06665 0.06065 -0.0419 1.0000 0.0743
-5.000 -0.2887 0.06343 0.05744 -0.0416 0.9981 0.0715
-4.750 -0.2486 0.05763 0.05135 -0.0495 0.9887 0.0680
-4.500 -0.2068 0.05253 0.04591 -0.0570 0.9792 0.0703
-4.250 -0.1649 0.04748 0.04043 -0.0634 0.9699 0.0697
-4.000 -0.1223 0.04281 0.03525 -0.0691 0.9610 0.0694
-3.750 -0.0777 0.03870 0.03040 -0.0743 0.9524 0.0736
-3.500 -0.0378 0.03531 0.02636 -0.0778 0.9425 0.0742
-3.250 0.0052 0.03237 0.02271 -0.0812 0.9346 0.0750
-3.000 0.0428 0.03068 0.02086 -0.0837 0.9247 0.0789
-2.750 0.0796 0.02922 0.01902 -0.0856 0.9137 0.0844
-2.500 0.1180 0.02755 0.01685 -0.0874 0.9039 0.0862
-2.250 0.1562 0.02617 0.01504 -0.0889 0.8941 0.0883
-2.000 0.1886 0.02521 0.01397 -0.0894 0.8820 0.0914
-1.750 0.2221 0.02442 0.01296 -0.0900 0.8701 0.0961
-1.500 0.2554 0.02371 0.01200 -0.0905 0.8585 0.1029
-1.250 0.2875 0.02316 0.01139 -0.0910 0.8469 0.1183
-1.000 0.3197 0.02252 0.01073 -0.0914 0.8358 0.1466
-0.750 0.3491 0.02170 0.01018 -0.0915 0.8234 0.2091
-0.500 0.3772 0.01914 0.00985 -0.0910 0.8115 1.0000
-0.250 0.4059 0.01926 0.00951 -0.0907 0.7987 1.0000
0.000 0.4341 0.01939 0.00929 -0.0903 0.7863 1.0000
0.250 0.4623 0.01951 0.00913 -0.0899 0.7743 1.0000
0.500 0.4908 0.01963 0.00898 -0.0896 0.7629 1.0000
0.750 0.5172 0.01984 0.00898 -0.0890 0.7501 1.0000
1.000 0.5437 0.02007 0.00904 -0.0886 0.7376 1.0000
1.250 0.5705 0.02030 0.00912 -0.0881 0.7254 1.0000
1.500 0.5974 0.02054 0.00921 -0.0877 0.7139 1.0000
1.750 0.6250 0.02075 0.00927 -0.0873 0.7030 1.0000
2.000 0.6509 0.02106 0.00951 -0.0868 0.6909 1.0000
2.250 0.6767 0.02140 0.00978 -0.0863 0.6787 1.0000
2.500 0.7027 0.02173 0.01005 -0.0859 0.6671 1.0000
2.750 0.7293 0.02204 0.01032 -0.0854 0.6564 1.0000
3.000 0.7556 0.02236 0.01060 -0.0850 0.6454 1.0000
3.250 0.7805 0.02278 0.01103 -0.0845 0.6333 1.0000
3.500 0.8057 0.02317 0.01145 -0.0840 0.6213 1.0000
3.750 0.8310 0.02352 0.01181 -0.0834 0.6094 1.0000
4.000 0.8566 0.02383 0.01212 -0.0827 0.5975 1.0000
4.250 0.8821 0.02411 0.01243 -0.0820 0.5852 1.0000
4.500 0.9061 0.02446 0.01283 -0.0812 0.5714 1.0000
4.750 0.9300 0.02479 0.01322 -0.0804 0.5572 1.0000
5.000 0.9538 0.02509 0.01358 -0.0795 0.5428 1.0000
5.250 0.9773 0.02540 0.01400 -0.0785 0.5283 1.0000
5.500 1.0007 0.02575 0.01443 -0.0777 0.5140 1.0000
5.750 1.0240 0.02617 0.01497 -0.0768 0.5006 1.0000
6.000 1.0472 0.02665 0.01563 -0.0761 0.4881 1.0000
6.250 1.0706 0.02713 0.01625 -0.0753 0.4759 1.0000
6.500 1.0939 0.02761 0.01687 -0.0744 0.4634 1.0000
6.750 1.1167 0.02809 0.01749 -0.0735 0.4502 1.0000
7.000 1.1391 0.02860 0.01819 -0.0726 0.4363 1.0000
7.250 1.1609 0.02916 0.01892 -0.0715 0.4219 1.0000
7.500 1.1823 0.02977 0.01972 -0.0705 0.4074 1.0000
7.750 1.2034 0.03046 0.02059 -0.0694 0.3931 1.0000
8.000 1.2222 0.03119 0.02152 -0.0680 0.3761 1.0000
8.250 1.2378 0.03171 0.02214 -0.0661 0.3535 1.0000
8.500 1.2503 0.03240 0.02300 -0.0640 0.3294 1.0000
8.750 1.2605 0.03316 0.02379 -0.0617 0.3037 1.0000
9.000 1.2671 0.03416 0.02484 -0.0592 0.2754 1.0000
9.250 1.2748 0.03534 0.02614 -0.0571 0.2525 1.0000
9.500 1.2801 0.03671 0.02761 -0.0548 0.2295 1.0000
9.750 1.2764 0.03852 0.02930 -0.0518 0.2013 1.0000
10.000 1.2688 0.04100 0.03158 -0.0494 0.1734 1.0000
10.250 1.2607 0.04402 0.03452 -0.0477 0.1420 1.0000
10.500 1.2550 0.04722 0.03772 -0.0467 0.0961 1.0000
10.750 1.2414 0.05148 0.04171 -0.0463 0.0784 1.0000
11.000 1.2307 0.05578 0.04598 -0.0461 0.0656 1.0000
11.250 1.2213 0.06014 0.05041 -0.0462 0.0573 1.0000
11.500 1.2115 0.06468 0.05502 -0.0465 0.0519 1.0000
11.750 1.2027 0.06923 0.05964 -0.0470 0.0482 1.0000
12.000 1.1949 0.07371 0.06434 -0.0477 0.0450 1.0000
12.250 1.1864 0.07840 0.06914 -0.0485 0.0426 1.0000
12.500 1.1770 0.08328 0.07410 -0.0495 0.0409 1.0000
12.750 1.1708 0.08776 0.07871 -0.0503 0.0391 1.0000
13.000 1.1653 0.09218 0.08328 -0.0512 0.0376 1.0000
13.250 1.1604 0.09656 0.08781 -0.0520 0.0363 1.0000
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Polar data table (+)
Polar graphs
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