GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 118 (MVA MK.7) AIRFOIL (goe118-il) Reynolds number: 50,000 Max Cl/Cd: 40.68 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe118-il-50000-n5.txt Download as CSV file: xf-goe118-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.2777 0.10752 0.10181 -0.0363 1.0000 0.0882
-7.500 -0.2923 0.10713 0.10158 -0.0335 1.0000 0.0893
-7.250 -0.3118 0.10728 0.10189 -0.0299 1.0000 0.0900
-7.000 -0.3029 0.10550 0.10017 -0.0374 0.9891 0.0917
-6.750 -0.2778 0.10227 0.09685 -0.0494 0.9753 0.0924
-6.250 -0.2322 0.09214 0.08669 -0.0591 0.9576 0.0929
-6.000 -0.2061 0.08787 0.08236 -0.0665 0.9468 0.0928
-5.750 -0.1763 0.08349 0.07785 -0.0742 0.9374 0.0923
-5.250 -0.1216 0.07037 0.06453 -0.0838 0.9212 0.0495
-5.000 -0.0908 0.06566 0.05972 -0.0890 0.9149 0.0479
-4.750 -0.0637 0.06138 0.05533 -0.0940 0.9046 0.0459
-4.500 -0.0281 0.05619 0.04993 -0.1011 0.8961 0.0429
-4.250 0.0184 0.04966 0.04295 -0.1104 0.8889 0.0392
-4.000 0.0507 0.04559 0.03859 -0.1144 0.8803 0.0383
-3.750 0.0916 0.04092 0.03342 -0.1196 0.8743 0.0375
-3.500 0.1268 0.03685 0.02878 -0.1230 0.8659 0.0371
-3.250 0.1690 0.03266 0.02374 -0.1266 0.8605 0.0384
-3.000 0.2005 0.03027 0.02081 -0.1279 0.8520 0.0419
-2.750 0.2376 0.02816 0.01816 -0.1294 0.8464 0.0457
-2.500 0.2665 0.02666 0.01616 -0.1292 0.8376 0.0498
-2.250 0.3009 0.02591 0.01520 -0.1301 0.8313 0.0668
-2.000 0.3306 0.02519 0.01419 -0.1300 0.8226 0.1027
-1.750 0.3604 0.02517 0.01396 -0.1305 0.8148 0.1767
-1.500 0.3890 0.02502 0.01360 -0.1309 0.8069 0.2186
-1.250 0.4169 0.02480 0.01307 -0.1308 0.7988 0.2238
-1.000 0.4470 0.02450 0.01253 -0.1310 0.7919 0.2314
-0.750 0.4733 0.02440 0.01228 -0.1309 0.7833 0.2418
-0.500 0.5037 0.02409 0.01185 -0.1312 0.7769 0.2619
-0.250 0.5289 0.02388 0.01187 -0.1311 0.7680 0.3171
0.000 0.5542 0.02223 0.01154 -0.1299 0.7621 1.0000
0.250 0.5784 0.02265 0.01160 -0.1294 0.7527 1.0000
0.500 0.6073 0.02283 0.01146 -0.1294 0.7460 1.0000
0.750 0.6322 0.02320 0.01162 -0.1291 0.7372 1.0000
1.000 0.6586 0.02350 0.01174 -0.1288 0.7295 1.0000
1.250 0.6853 0.02377 0.01185 -0.1286 0.7218 1.0000
1.500 0.7098 0.02417 0.01215 -0.1282 0.7133 1.0000
1.750 0.7378 0.02436 0.01223 -0.1281 0.7064 1.0000
2.000 0.7607 0.02486 0.01273 -0.1276 0.6972 1.0000
2.250 0.7898 0.02499 0.01278 -0.1275 0.6910 1.0000
2.500 0.8113 0.02558 0.01340 -0.1269 0.6814 1.0000
2.750 0.8384 0.02584 0.01365 -0.1267 0.6746 1.0000
3.250 0.8856 0.02681 0.01481 -0.1257 0.6581 1.0000
3.500 0.9106 0.02722 0.01531 -0.1253 0.6506 1.0000
3.750 0.9328 0.02783 0.01607 -0.1247 0.6423 1.0000
4.000 0.9592 0.02817 0.01660 -0.1243 0.6356 1.0000
4.250 0.9795 0.02895 0.01759 -0.1236 0.6269 1.0000
4.500 1.0066 0.02927 0.01812 -0.1233 0.6208 1.0000
4.750 1.0251 0.03021 0.01934 -0.1223 0.6119 1.0000
5.000 1.0508 0.03028 0.01974 -0.1214 0.6018 1.0000
5.250 1.0730 0.02756 0.01699 -0.1163 0.5548 1.0000
5.500 1.0837 0.02664 0.01595 -0.1114 0.4973 1.0000
5.750 1.0914 0.02688 0.01599 -0.1072 0.4258 1.0000
6.000 1.0861 0.02861 0.01660 -0.1020 0.2684 1.0000
6.250 1.0615 0.03280 0.01947 -0.0967 0.0803 1.0000
6.500 1.0584 0.03540 0.02189 -0.0935 0.0482 1.0000
6.750 1.0617 0.03754 0.02417 -0.0912 0.0431 1.0000
7.000 1.0614 0.04007 0.02692 -0.0889 0.0394 1.0000
7.250 1.0627 0.04255 0.02966 -0.0871 0.0363 1.0000
7.500 1.0608 0.04545 0.03278 -0.0855 0.0341 1.0000
7.750 1.0570 0.04865 0.03619 -0.0841 0.0329 1.0000
8.000 1.0519 0.05210 0.03984 -0.0829 0.0322 1.0000
8.250 1.0505 0.05520 0.04314 -0.0817 0.0317 1.0000
8.500 1.0497 0.05823 0.04639 -0.0805 0.0312 1.0000
8.750 1.0503 0.06107 0.04942 -0.0792 0.0304 1.0000
9.000 1.0532 0.06354 0.05207 -0.0775 0.0293 1.0000
9.250 1.0603 0.06541 0.05408 -0.0753 0.0276 1.0000
9.500 1.0822 0.06557 0.05428 -0.0715 0.0258 1.0000
9.750 1.2536 0.06262 0.05170 -0.0684 0.0254 1.0000
10.000 1.3175 0.06927 0.05862 -0.0720 0.0242 1.0000
10.250 1.3338 0.07380 0.06350 -0.0710 0.0240 1.0000
10.500 1.3328 0.07623 0.06631 -0.0679 0.0243 1.0000
10.750 1.3186 0.07800 0.06851 -0.0637 0.0247 1.0000
11.000 1.3057 0.08045 0.07139 -0.0604 0.0253 1.0000
11.250 1.2947 0.08366 0.07498 -0.0580 0.0260 1.0000
11.500 1.2820 0.08729 0.07895 -0.0562 0.0266 1.0000
11.750 1.2684 0.09126 0.08323 -0.0550 0.0272 1.0000
12.000 1.2539 0.09552 0.08777 -0.0544 0.0277 1.0000
12.250 1.2384 0.10006 0.09257 -0.0543 0.0281 1.0000
12.500 1.2222 0.10488 0.09762 -0.0549 0.0285 1.0000
12.750 1.2055 0.10999 0.10295 -0.0560 0.0288 1.0000
13.000 1.1886 0.11541 0.10857 -0.0578 0.0291 1.0000
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Polar data table (+)
Polar graphs
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