GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 500,000 Max Cl/Cd: 108.94 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe118-il-500000-n5.txt Download as CSV file: xf-goe118-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 118 (MVA MK.7) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2245 0.09991 0.09755 -0.0487 0.8845 0.0061
-8.500 -0.2179 0.09701 0.09456 -0.0500 0.8623 0.0062
-8.250 -0.2109 0.09407 0.09154 -0.0515 0.8430 0.0062
-8.000 -0.2035 0.09101 0.08842 -0.0532 0.8253 0.0063
-7.750 -0.1958 0.08787 0.08522 -0.0550 0.8096 0.0063
-7.500 -0.1876 0.08468 0.08195 -0.0569 0.7953 0.0063
-7.250 -0.1793 0.08152 0.07874 -0.0591 0.7825 0.0063
-7.000 -0.1724 0.07689 0.07408 -0.0627 0.7718 0.0065
-6.500 -0.1443 0.06984 0.06693 -0.0700 0.7524 0.0068
-6.250 -0.1267 0.06631 0.06335 -0.0743 0.7439 0.0069
-6.000 -0.1064 0.06260 0.05958 -0.0792 0.7356 0.0071
-5.750 -0.0834 0.05864 0.05556 -0.0847 0.7282 0.0073
-4.750 0.0400 0.03872 0.03515 -0.1107 0.7022 0.0056
-4.500 0.0747 0.03298 0.02917 -0.1164 0.6961 0.0050
-4.250 0.1142 0.02301 0.01858 -0.1222 0.6916 0.0043
-4.000 0.1471 0.01769 0.01242 -0.1242 0.6864 0.0040
-3.750 0.1762 0.01560 0.00986 -0.1248 0.6802 0.0041
-3.500 0.2049 0.01424 0.00813 -0.1251 0.6743 0.0044
-3.250 0.2336 0.01314 0.00674 -0.1253 0.6678 0.0049
-3.000 0.2619 0.01274 0.00612 -0.1253 0.6618 0.0061
-2.750 0.2905 0.01164 0.00482 -0.1255 0.6555 0.0066
-2.500 0.3187 0.01080 0.00381 -0.1256 0.6492 0.0071
-2.250 0.3471 0.01032 0.00325 -0.1258 0.6430 0.0081
-2.000 0.3753 0.01003 0.00285 -0.1259 0.6362 0.0099
-1.750 0.4037 0.00972 0.00238 -0.1260 0.6295 0.0129
-1.500 0.4318 0.00950 0.00203 -0.1261 0.6212 0.0186
-1.250 0.4598 0.00920 0.00180 -0.1263 0.6124 0.0710
-1.000 0.4875 0.00923 0.00178 -0.1264 0.6042 0.0898
-0.750 0.5154 0.00923 0.00175 -0.1266 0.5967 0.0987
-0.500 0.5431 0.00925 0.00171 -0.1267 0.5903 0.1037
-0.250 0.5711 0.00923 0.00164 -0.1269 0.5838 0.1052
0.000 0.5987 0.00925 0.00158 -0.1269 0.5765 0.1067
0.250 0.6264 0.00924 0.00155 -0.1271 0.5663 0.1106
0.500 0.6539 0.00926 0.00154 -0.1272 0.5568 0.1154
1.000 0.7090 0.00932 0.00158 -0.1274 0.5404 0.1324
1.250 0.7364 0.00934 0.00162 -0.1275 0.5326 0.1512
1.500 0.7639 0.00924 0.00170 -0.1278 0.5239 0.2278
1.750 0.7905 0.00860 0.00194 -0.1282 0.5154 0.6005
2.250 0.8409 0.00803 0.00208 -0.1272 0.4983 1.0000
2.500 0.8679 0.00818 0.00220 -0.1273 0.4908 1.0000
2.750 0.8949 0.00832 0.00232 -0.1273 0.4794 1.0000
3.250 0.9478 0.00870 0.00261 -0.1272 0.4496 1.0000
3.500 0.9714 0.00916 0.00287 -0.1267 0.4051 1.0000
3.750 0.9911 0.01006 0.00334 -0.1257 0.3258 1.0000
4.000 0.9997 0.01224 0.00456 -0.1232 0.1394 1.0000
4.250 1.0165 0.01349 0.00544 -0.1217 0.0219 1.0000
4.500 1.0405 0.01391 0.00592 -0.1211 0.0129 1.0000
4.750 1.0630 0.01450 0.00661 -0.1203 0.0084 1.0000
5.000 1.0855 0.01504 0.00725 -0.1195 0.0073 1.0000
5.250 1.1080 0.01552 0.00774 -0.1188 0.0057 1.0000
5.500 1.1264 0.01641 0.00874 -0.1174 0.0049 1.0000
5.750 1.1439 0.01731 0.00978 -0.1158 0.0044 1.0000
6.000 1.1585 0.01839 0.01098 -0.1137 0.0041 1.0000
6.250 1.1699 0.01962 0.01232 -0.1111 0.0039 1.0000
6.500 1.1786 0.02095 0.01376 -0.1082 0.0037 1.0000
6.750 1.1871 0.02204 0.01492 -0.1052 0.0035 1.0000
7.000 1.1940 0.02325 0.01617 -0.1024 0.0031 1.0000
7.250 1.2014 0.02462 0.01767 -0.0994 0.0027 1.0000
7.500 1.2074 0.02647 0.01962 -0.0962 0.0025 1.0000
7.750 1.2219 0.02845 0.02168 -0.0938 0.0023 1.0000
8.000 1.2552 0.03092 0.02423 -0.0937 0.0021 1.0000
8.250 1.3017 0.03450 0.02802 -0.0958 0.0022 1.0000
8.500 1.3316 0.03796 0.03171 -0.0954 0.0023 1.0000
8.750 1.3519 0.04121 0.03521 -0.0939 0.0025 1.0000
9.000 1.3660 0.04441 0.03865 -0.0919 0.0026 1.0000
9.250 1.3738 0.04767 0.04214 -0.0896 0.0028 1.0000
13.750 1.1464 0.12680 0.12451 -0.0723 0.0039 1.0000
14.000 1.1293 0.13473 0.13255 -0.0771 0.0039 1.0000
14.250 1.1134 0.14330 0.14122 -0.0826 0.0040 1.0000
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Polar data table (+)
Polar graphs
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