GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 100,000 Max Cl/Cd: 62 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe118-il-100000.txt Download as CSV file: xf-goe118-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3064 0.10166 0.09765 -0.0320 1.0000 0.0688
-7.250 -0.3324 0.10231 0.09845 -0.0265 1.0000 0.0688
-7.000 -0.3563 0.10278 0.09904 -0.0221 1.0000 0.0688
-6.750 -0.3159 0.09915 0.09539 -0.0458 0.9860 0.0705
-6.500 -0.3040 0.09244 0.08868 -0.0372 0.9851 0.0731
-6.250 -0.2767 0.08799 0.08420 -0.0427 0.9774 0.0776
-6.000 -0.2206 0.08429 0.08033 -0.0703 0.9625 0.0836
-5.750 -0.2112 0.07823 0.07435 -0.0633 0.9594 0.0859
-5.500 -0.1819 0.07399 0.07006 -0.0678 0.9525 0.0916
-5.250 -0.1357 0.06861 0.06455 -0.0827 0.9438 0.0988
-5.000 -0.1125 0.06497 0.06089 -0.0838 0.9359 0.1058
-4.750 -0.0618 0.05934 0.05507 -0.0967 0.9301 0.1132
-4.500 -0.0332 0.05555 0.05117 -0.0999 0.9213 0.1171
-4.250 0.0230 0.05024 0.04548 -0.1122 0.9160 0.1260
-4.000 0.0497 0.04665 0.04183 -0.1141 0.9067 0.1284
-3.750 0.1182 0.03623 0.03026 -0.1260 0.9027 0.0695
-3.500 0.1544 0.03032 0.02347 -0.1288 0.8942 0.0582
-3.250 0.1943 0.02651 0.01915 -0.1316 0.8893 0.0565
-3.000 0.2261 0.02410 0.01610 -0.1322 0.8804 0.0586
-2.750 0.2630 0.02263 0.01442 -0.1335 0.8749 0.0651
-2.500 0.2915 0.02121 0.01262 -0.1331 0.8653 0.0701
-2.250 0.3230 0.02024 0.01155 -0.1332 0.8579 0.0845
-2.000 0.3528 0.01986 0.01118 -0.1332 0.8495 0.1431
-1.750 0.3792 0.01985 0.01102 -0.1330 0.8402 0.1828
-1.500 0.4092 0.01964 0.01073 -0.1333 0.8338 0.2131
-1.250 0.4340 0.01966 0.01062 -0.1329 0.8236 0.2349
-1.000 0.4608 0.01937 0.01031 -0.1326 0.8152 0.2405
-0.750 0.4890 0.01907 0.00990 -0.1322 0.8078 0.2483
-0.500 0.5139 0.01894 0.00979 -0.1316 0.7984 0.2598
-0.250 0.5424 0.01861 0.00950 -0.1313 0.7913 0.2831
0.000 0.5668 0.01677 0.00944 -0.1304 0.7826 1.0000
0.250 0.5938 0.01700 0.00927 -0.1298 0.7739 1.0000
0.500 0.6219 0.01708 0.00909 -0.1294 0.7666 1.0000
0.750 0.6468 0.01740 0.00927 -0.1289 0.7569 1.0000
1.000 0.6738 0.01758 0.00930 -0.1286 0.7493 1.0000
1.250 0.7001 0.01780 0.00942 -0.1282 0.7409 1.0000
1.500 0.7253 0.01814 0.00969 -0.1278 0.7322 1.0000
1.750 0.7533 0.01825 0.00969 -0.1275 0.7255 1.0000
2.000 0.7775 0.01867 0.01010 -0.1271 0.7160 1.0000
2.250 0.8045 0.01889 0.01031 -0.1268 0.7091 1.0000
2.500 0.8299 0.01923 0.01065 -0.1265 0.7005 1.0000
2.750 0.8550 0.01961 0.01106 -0.1261 0.6923 1.0000
3.000 0.8823 0.01981 0.01125 -0.1258 0.6853 1.0000
3.250 0.9062 0.02030 0.01182 -0.1254 0.6762 1.0000
3.500 0.9349 0.02041 0.01199 -0.1252 0.6702 1.0000
3.750 0.9576 0.02099 0.01272 -0.1247 0.6606 1.0000
4.000 0.9829 0.02121 0.01304 -0.1241 0.6511 1.0000
4.250 1.0099 0.01953 0.01120 -0.1213 0.6237 1.0000
4.500 1.0359 0.01863 0.01022 -0.1194 0.6011 1.0000
4.750 1.0570 0.01791 0.00959 -0.1169 0.5688 1.0000
5.000 1.0762 0.01746 0.00910 -0.1142 0.5269 1.0000
5.250 1.0894 0.01757 0.00889 -0.1108 0.4459 1.0000
5.500 1.0901 0.01944 0.00961 -0.1064 0.2745 1.0000
5.750 1.0810 0.02306 0.01195 -0.1017 0.0666 1.0000
6.000 1.0958 0.02432 0.01333 -0.0995 0.0561 1.0000
6.250 1.1099 0.02553 0.01475 -0.0973 0.0519 1.0000
6.500 1.1179 0.02712 0.01653 -0.0945 0.0489 1.0000
6.750 1.1244 0.02864 0.01826 -0.0915 0.0460 1.0000
7.000 1.1263 0.03021 0.01999 -0.0880 0.0441 1.0000
7.250 1.1266 0.03200 0.02199 -0.0846 0.0437 1.0000
7.500 1.1281 0.03389 0.02396 -0.0814 0.0436 1.0000
7.750 1.1355 0.03568 0.02576 -0.0786 0.0438 1.0000
8.000 1.1642 0.03729 0.02725 -0.0769 0.0450 1.0000
8.250 1.2528 0.04063 0.03038 -0.0823 0.0496 1.0000
8.500 1.2911 0.04299 0.03312 -0.0820 0.0522 1.0000
8.750 1.3415 0.04655 0.03704 -0.0828 0.0623 1.0000
10.500 1.3102 0.08235 0.07847 -0.0639 0.2389 1.0000
10.750 1.2748 0.08677 0.08291 -0.0631 0.2273 1.0000
11.000 1.2403 0.09258 0.08873 -0.0640 0.2168 1.0000
11.250 1.2074 0.10070 0.09686 -0.0670 0.2136 1.0000
11.500 1.1731 0.10841 0.10453 -0.0703 0.2020 1.0000
11.750 1.0749 0.09519 0.09140 -0.0438 0.1757 1.0000
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Polar data table (+)
Polar graphs
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