GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 116 (MVA MK.3) AIRFOIL (goe116-il) Reynolds number: 500,000 Max Cl/Cd: 106.83 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe116-il-500000.txt Download as CSV file: xf-goe116-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 116 (MVA MK.3) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4140 0.11447 0.11229 -0.0220 1.0000 0.0133
-10.250 -0.4240 0.10736 0.10522 -0.0243 1.0000 0.0139
-10.000 -0.4221 0.10342 0.10131 -0.0259 1.0000 0.0143
-9.750 -0.4174 0.10017 0.09807 -0.0273 1.0000 0.0147
-9.500 -0.4129 0.09685 0.09477 -0.0288 1.0000 0.0150
-5.750 -0.2355 0.01702 0.01139 -0.0921 0.8009 0.0199
-5.500 -0.2086 0.01515 0.00924 -0.0918 0.7931 0.0174
-5.250 -0.1808 0.01406 0.00788 -0.0914 0.7863 0.0155
-5.000 -0.1530 0.01328 0.00692 -0.0913 0.7790 0.0150
-4.750 -0.1252 0.01250 0.00598 -0.0913 0.7727 0.0152
-4.500 -0.0971 0.01177 0.00511 -0.0914 0.7660 0.0161
-4.250 -0.0690 0.01126 0.00442 -0.0914 0.7604 0.0173
-4.000 -0.0404 0.01083 0.00384 -0.0916 0.7541 0.0189
-3.750 -0.0120 0.01054 0.00337 -0.0916 0.7486 0.0208
-3.500 0.0167 0.01030 0.00301 -0.0917 0.7431 0.0239
-3.250 0.0444 0.00964 0.00277 -0.0919 0.7376 0.1243
-3.000 0.0735 0.01007 0.00310 -0.0920 0.7328 0.1425
-2.750 0.1025 0.01029 0.00332 -0.0923 0.7272 0.1506
-2.500 0.1313 0.01048 0.00340 -0.0924 0.7222 0.1553
-2.250 0.1595 0.01042 0.00334 -0.0926 0.7176 0.1607
-2.000 0.1884 0.01074 0.00360 -0.0928 0.7124 0.1679
-1.750 0.2164 0.01049 0.00334 -0.0930 0.7078 0.1719
-1.500 0.2448 0.01036 0.00318 -0.0932 0.7034 0.1729
-1.250 0.2732 0.01022 0.00304 -0.0934 0.6985 0.1741
-1.000 0.3016 0.01012 0.00290 -0.0935 0.6942 0.1754
-0.750 0.3300 0.01005 0.00280 -0.0937 0.6902 0.1767
-0.500 0.3585 0.00995 0.00272 -0.0939 0.6856 0.1781
-0.250 0.3869 0.00989 0.00264 -0.0941 0.6814 0.1795
0.000 0.4153 0.00987 0.00258 -0.0942 0.6776 0.1809
0.250 0.4439 0.00983 0.00257 -0.0944 0.6732 0.1822
0.500 0.4722 0.00968 0.00246 -0.0946 0.6691 0.1846
0.750 0.5005 0.00963 0.00242 -0.0948 0.6653 0.1866
1.000 0.5290 0.00960 0.00244 -0.0950 0.6611 0.1887
1.250 0.5574 0.00956 0.00244 -0.0952 0.6561 0.1910
1.500 0.5857 0.00955 0.00243 -0.0953 0.6512 0.1936
1.750 0.6140 0.00953 0.00245 -0.0955 0.6455 0.1960
2.000 0.6423 0.00946 0.00246 -0.0957 0.6400 0.2002
2.250 0.6705 0.00947 0.00251 -0.0958 0.6353 0.2048
2.750 0.7266 0.00939 0.00257 -0.0960 0.6202 0.2192
3.000 0.7539 0.00925 0.00254 -0.0959 0.6025 0.2370
3.250 0.7765 0.00757 0.00268 -0.0951 0.5912 1.0000
3.500 0.8040 0.00763 0.00272 -0.0950 0.5754 1.0000
3.750 0.8301 0.00777 0.00273 -0.0946 0.5382 1.0000
4.000 0.8507 0.00857 0.00296 -0.0935 0.4199 1.0000
4.500 0.8739 0.01290 0.00539 -0.0894 0.0223 1.0000
4.750 0.8985 0.01334 0.00591 -0.0888 0.0197 1.0000
5.000 0.9220 0.01392 0.00657 -0.0881 0.0179 1.0000
5.250 0.9438 0.01466 0.00738 -0.0871 0.0165 1.0000
5.500 0.9628 0.01566 0.00847 -0.0857 0.0154 1.0000
5.750 0.9788 0.01691 0.00982 -0.0837 0.0148 1.0000
6.000 0.9900 0.01863 0.01163 -0.0811 0.0138 1.0000
6.250 1.0112 0.01928 0.01234 -0.0800 0.0133 1.0000
6.500 1.0290 0.02040 0.01351 -0.0784 0.0129 1.0000
6.750 1.0474 0.02172 0.01489 -0.0768 0.0126 1.0000
7.000 1.0683 0.02343 0.01665 -0.0754 0.0125 1.0000
9.250 1.2311 0.05242 0.04751 -0.0632 0.0138 1.0000
9.500 1.2342 0.05365 0.04902 -0.0600 0.0136 1.0000
9.750 1.2500 0.05208 0.04764 -0.0575 0.0121 1.0000
10.000 1.2517 0.05452 0.05031 -0.0546 0.0113 1.0000
10.250 1.2475 0.05724 0.05324 -0.0514 0.0109 1.0000
10.500 1.2367 0.05979 0.05596 -0.0475 0.0106 1.0000
10.750 1.2235 0.06258 0.05892 -0.0443 0.0104 1.0000
11.000 1.2087 0.06571 0.06222 -0.0417 0.0102 1.0000
11.250 1.1929 0.06923 0.06594 -0.0400 0.0101 1.0000
11.500 1.1760 0.07316 0.07003 -0.0390 0.0101 1.0000
11.750 1.1580 0.07753 0.07455 -0.0386 0.0100 1.0000
12.000 1.1388 0.08244 0.07962 -0.0390 0.0100 1.0000
12.250 1.1186 0.08787 0.08517 -0.0402 0.0100 1.0000
12.500 1.0973 0.09394 0.09139 -0.0422 0.0100 1.0000
12.750 1.0747 0.10081 0.09840 -0.0451 0.0101 1.0000
13.000 1.0510 0.10873 0.10646 -0.0493 0.0102 1.0000
13.250 1.0265 0.11815 0.11601 -0.0550 0.0105 1.0000
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Polar data table (+)
Polar graphs
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