GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 165 (MVA MK.11) AIRFOIL (goe165-il) Reynolds number: 50,000 Max Cl/Cd: 31.33 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe165-il-50000.txt Download as CSV file: xf-goe165-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 165 (MVA MK.11) 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2824 0.11332 0.10700 -0.0235 1.0000 0.2411
-8.000 -0.2712 0.10979 0.10351 -0.0225 1.0000 0.2482
-7.750 -0.2959 0.11107 0.10500 -0.0219 1.0000 0.2538
-7.500 -0.2698 0.10497 0.09888 -0.0208 1.0000 0.2596
-7.250 -0.2851 0.10490 0.09897 -0.0194 1.0000 0.2672
-7.000 -0.2796 0.10137 0.09552 -0.0183 1.0000 0.2705
-6.750 -0.2745 0.09854 0.09276 -0.0168 1.0000 0.2757
-6.500 -0.2958 0.09869 0.09310 -0.0141 1.0000 0.2811
-6.250 -0.3089 0.09733 0.09192 -0.0121 1.0000 0.2830
-6.000 -0.3039 0.09400 0.08866 -0.0103 1.0000 0.2850
-5.750 -0.3068 0.09178 0.08655 -0.0085 1.0000 0.2870
-5.500 -0.3144 0.08999 0.08489 -0.0068 1.0000 0.2882
-5.250 -0.3338 0.06549 0.06037 -0.0513 1.0000 0.1273
-5.000 -0.3234 0.06229 0.05718 -0.0513 1.0000 0.1205
-4.750 -0.2115 0.03962 0.03226 -0.0946 1.0000 0.0997
-4.500 -0.1798 0.03681 0.02913 -0.0973 1.0000 0.1021
-4.250 -0.1469 0.03448 0.02638 -0.0997 1.0000 0.1042
-4.000 -0.1163 0.03273 0.02427 -0.1010 1.0000 0.1060
-3.750 -0.0879 0.03150 0.02274 -0.1015 1.0000 0.1095
-3.500 -0.0611 0.03040 0.02161 -0.1017 1.0000 0.1157
-3.250 -0.0306 0.02935 0.02064 -0.1031 1.0000 0.1323
-3.000 0.0122 0.02781 0.01981 -0.1072 1.0000 0.1929
-2.750 0.0070 0.03165 0.02463 -0.0989 1.0000 0.3563
-2.500 -0.0021 0.03553 0.02862 -0.0897 1.0000 0.4131
-2.250 -0.0083 0.03783 0.03109 -0.0815 1.0000 0.4572
-2.000 0.0037 0.03906 0.03234 -0.0764 0.9942 0.5070
-1.750 0.0438 0.03911 0.03213 -0.0780 0.9805 0.5509
-1.500 0.0900 0.03873 0.03148 -0.0818 0.9661 0.5860
-1.250 0.1374 0.03810 0.03062 -0.0860 0.9511 0.6086
-1.000 0.1968 0.03744 0.02962 -0.0933 0.9354 0.6191
-0.750 0.2581 0.03681 0.02869 -0.1010 0.9188 0.6262
-0.500 0.3087 0.03612 0.02778 -0.1062 0.8997 0.6324
-0.250 0.3654 0.03536 0.02681 -0.1120 0.8811 0.6416
0.000 0.4220 0.03426 0.02557 -0.1170 0.8633 0.6502
0.250 0.4722 0.03339 0.02456 -0.1209 0.8419 0.6593
0.500 0.5299 0.03207 0.02313 -0.1253 0.8229 0.6700
0.750 0.5888 0.03055 0.02149 -0.1292 0.8047 0.6813
1.000 0.6342 0.02961 0.02044 -0.1313 0.7804 0.6913
1.250 0.6891 0.02838 0.01905 -0.1344 0.7599 0.7026
1.500 0.7256 0.02798 0.01854 -0.1350 0.7335 0.7122
1.750 0.7620 0.02783 0.01826 -0.1358 0.7090 0.7213
2.000 0.7985 0.02784 0.01813 -0.1368 0.6875 0.7310
2.250 0.8287 0.02812 0.01833 -0.1370 0.6681 0.7401
2.500 0.8560 0.02868 0.01886 -0.1371 0.6498 0.7490
2.750 0.8834 0.02920 0.01937 -0.1372 0.6341 0.7591
3.000 0.9104 0.02974 0.01996 -0.1372 0.6205 0.7700
3.250 0.9395 0.03019 0.02042 -0.1374 0.6092 0.7826
3.500 0.9617 0.03102 0.02140 -0.1370 0.5977 0.7967
3.750 0.9819 0.03195 0.02253 -0.1363 0.5872 0.8164
4.000 1.0074 0.03227 0.02307 -0.1357 0.5790 0.8683
4.250 1.0296 0.03366 0.02457 -0.1361 0.5691 1.0000
4.500 1.0545 0.03515 0.02609 -0.1368 0.5612 1.0000
4.750 1.0794 0.03657 0.02755 -0.1374 0.5537 1.0000
5.000 1.0996 0.03833 0.02943 -0.1375 0.5464 1.0000
5.250 1.1203 0.04000 0.03117 -0.1376 0.5392 1.0000
5.500 1.1406 0.04180 0.03305 -0.1375 0.5334 1.0000
5.750 1.1449 0.04489 0.03631 -0.1365 0.5266 1.0000
6.000 1.1758 0.04555 0.03698 -0.1367 0.5199 1.0000
6.250 1.1590 0.05051 0.04214 -0.1344 0.5127 1.0000
6.500 1.1962 0.05033 0.04201 -0.1345 0.5051 1.0000
6.750 1.1142 0.06231 0.05415 -0.1312 0.5024 1.0000
7.000 1.0250 0.07657 0.06837 -0.1321 0.5029 1.0000
7.250 0.9960 0.08381 0.07563 -0.1329 0.5013 1.0000
7.500 1.0258 0.08426 0.07614 -0.1318 0.4900 1.0000
7.750 0.9978 0.09095 0.08284 -0.1323 0.4860 1.0000
8.000 1.0160 0.09235 0.08430 -0.1311 0.4733 1.0000
8.250 1.0370 0.09330 0.08535 -0.1297 0.4598 1.0000
8.500 1.0212 0.09891 0.09100 -0.1302 0.4545 1.0000
8.750 1.0317 0.10139 0.09355 -0.1294 0.4442 1.0000
9.000 1.0553 0.10223 0.09449 -0.1279 0.4316 1.0000
9.250 1.0307 0.10947 0.10175 -0.1294 0.4301 1.0000
9.500 1.0153 0.11568 0.10801 -0.1308 0.4290 1.0000
9.750 1.0052 0.12150 0.11388 -0.1321 0.4295 1.0000
10.000 1.0010 0.12693 0.11938 -0.1335 0.4311 1.0000
10.250 1.0045 0.13192 0.12445 -0.1347 0.4328 1.0000
10.500 1.0117 0.13417 0.12676 -0.1337 0.4174 1.0000
10.750 1.5101 0.04820 0.04178 -0.0966 0.2665 1.0000
11.000 1.4911 0.05014 0.04399 -0.0919 0.2510 1.0000
11.250 1.4695 0.05315 0.04724 -0.0887 0.2331 1.0000
11.500 1.4481 0.05713 0.05144 -0.0871 0.2115 1.0000
11.750 1.4271 0.06202 0.05647 -0.0869 0.1843 1.0000
12.000 1.4075 0.06669 0.06069 -0.0867 0.1464 1.0000
12.250 1.3848 0.07275 0.06656 -0.0875 0.1322 1.0000
12.500 1.3619 0.07924 0.07298 -0.0887 0.1230 1.0000
12.750 1.3406 0.08579 0.07952 -0.0901 0.1149 1.0000
13.000 1.3206 0.09219 0.08581 -0.0915 0.1083 1.0000
13.250 1.3049 0.09823 0.09185 -0.0929 0.1000 1.0000
13.500 1.2914 0.10384 0.09735 -0.0941 0.0932 1.0000
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Polar data table (+)
Polar graphs
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