GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Reynolds number: 100,000 Max Cl/Cd: 60.78 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe164-il-100000.txt Download as CSV file: xf-goe164-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 164 (MVA MK.10) 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
------ -------- --------- --------- -------- -------- --------
-6.750 -0.2999 0.09895 0.09479 -0.0187 1.0000 0.0853
-6.500 -0.3147 0.09909 0.09508 -0.0203 1.0000 0.0868
-6.250 -0.3243 0.09929 0.09538 -0.0255 1.0000 0.0874
-6.000 -0.3225 0.09411 0.09025 -0.0163 1.0000 0.0893
-5.750 -0.3241 0.09223 0.08843 -0.0131 1.0000 0.0919
-5.500 -0.3276 0.09074 0.08700 -0.0121 1.0000 0.0946
-5.250 -0.3010 0.08868 0.08492 -0.0299 0.9966 0.1007
-5.000 -0.2886 0.08392 0.08019 -0.0247 0.9925 0.1029
-4.750 -0.2520 0.08001 0.07624 -0.0313 0.9855 0.1105
-4.500 -0.2104 0.07507 0.07124 -0.0421 0.9767 0.1163
-4.250 -0.1487 0.07042 0.06642 -0.0592 0.9680 0.1280
-4.000 -0.1298 0.06674 0.06278 -0.0569 0.9613 0.1320
-3.750 -0.0756 0.06207 0.05796 -0.0693 0.9519 0.1434
-3.500 0.0398 0.04313 0.03805 -0.1026 0.9500 0.0873
-3.250 0.0967 0.03740 0.03205 -0.1110 0.9459 0.0839
-3.000 0.1755 0.02730 0.02040 -0.1249 0.9461 0.0834
-2.750 0.2220 0.02500 0.01761 -0.1286 0.9368 0.0922
-2.500 0.2719 0.02348 0.01582 -0.1324 0.9293 0.1056
-2.250 0.3165 0.02262 0.01479 -0.1349 0.9191 0.1284
-2.000 0.3544 0.02268 0.01498 -0.1360 0.9068 0.1619
-1.750 0.3918 0.02269 0.01497 -0.1371 0.8960 0.2171
-1.500 0.4358 0.02229 0.01460 -0.1396 0.8899 0.2500
-1.250 0.4712 0.02197 0.01418 -0.1406 0.8788 0.2756
-1.000 0.5087 0.02146 0.01373 -0.1419 0.8690 0.2972
-0.750 0.5543 0.02050 0.01254 -0.1446 0.8615 0.3076
-0.500 0.5915 0.01978 0.01171 -0.1458 0.8494 0.3127
-0.250 0.6304 0.01914 0.01086 -0.1473 0.8370 0.3194
0.000 0.6680 0.01853 0.01019 -0.1485 0.8236 0.3268
0.250 0.7040 0.01810 0.00959 -0.1494 0.8083 0.3343
0.500 0.7372 0.01775 0.00917 -0.1497 0.7915 0.3414
0.750 0.7687 0.01756 0.00883 -0.1498 0.7737 0.3511
1.000 0.7985 0.01740 0.00860 -0.1495 0.7556 0.3626
1.250 0.8245 0.01732 0.00848 -0.1485 0.7362 0.3743
1.500 0.8508 0.01726 0.00837 -0.1477 0.7170 0.3880
1.750 0.8772 0.01718 0.00824 -0.1468 0.6983 0.4074
2.000 0.9033 0.01702 0.00812 -0.1460 0.6800 0.4367
2.250 0.9271 0.01667 0.00813 -0.1448 0.6604 0.5142
2.500 0.9501 0.01609 0.00799 -0.1431 0.6400 1.0000
2.750 0.9757 0.01632 0.00796 -0.1421 0.6199 1.0000
3.000 1.0000 0.01661 0.00806 -0.1410 0.5992 1.0000
3.250 1.0245 0.01693 0.00823 -0.1400 0.5796 1.0000
3.500 1.0494 0.01729 0.00845 -0.1392 0.5619 1.0000
3.750 1.0743 0.01768 0.00869 -0.1384 0.5453 1.0000
4.000 1.0989 0.01808 0.00896 -0.1376 0.5292 1.0000
4.250 1.1232 0.01848 0.00925 -0.1367 0.5138 1.0000
4.500 1.1471 0.01888 0.00961 -0.1358 0.4989 1.0000
4.750 1.1709 0.01930 0.00998 -0.1349 0.4850 1.0000
5.000 1.1945 0.01971 0.01038 -0.1340 0.4717 1.0000
5.250 1.2182 0.02014 0.01080 -0.1332 0.4595 1.0000
5.500 1.2423 0.02059 0.01125 -0.1324 0.4484 1.0000
5.750 1.2668 0.02104 0.01165 -0.1317 0.4378 1.0000
6.000 1.2896 0.02152 0.01221 -0.1308 0.4266 1.0000
6.250 1.3131 0.02204 0.01280 -0.1300 0.4164 1.0000
6.500 1.3377 0.02256 0.01329 -0.1293 0.4069 1.0000
6.750 1.3599 0.02312 0.01395 -0.1283 0.3962 1.0000
7.000 1.3826 0.02374 0.01465 -0.1274 0.3860 1.0000
7.250 1.4068 0.02439 0.01530 -0.1268 0.3764 1.0000
7.500 1.4288 0.02507 0.01610 -0.1258 0.3660 1.0000
7.750 1.4507 0.02586 0.01701 -0.1248 0.3561 1.0000
8.000 1.4758 0.02665 0.01777 -0.1244 0.3473 1.0000
8.250 1.4946 0.02730 0.01861 -0.1229 0.3358 1.0000
8.500 1.5116 0.02781 0.01923 -0.1210 0.3228 1.0000
8.750 1.5274 0.02824 0.01976 -0.1190 0.3096 1.0000
9.000 1.5433 0.02868 0.02030 -0.1170 0.2977 1.0000
9.250 1.5593 0.02907 0.02076 -0.1150 0.2865 1.0000
9.500 1.5702 0.02940 0.02132 -0.1122 0.2739 1.0000
9.750 1.5787 0.02972 0.02188 -0.1091 0.2601 1.0000
10.000 1.5863 0.03010 0.02248 -0.1058 0.2455 1.0000
10.250 1.5887 0.03056 0.02311 -0.1018 0.2248 1.0000
10.500 1.5857 0.03149 0.02402 -0.0973 0.1974 1.0000
10.750 1.5758 0.03340 0.02573 -0.0926 0.1665 1.0000
11.250 1.5390 0.04006 0.03178 -0.0839 0.0832 1.0000
11.500 1.5179 0.04420 0.03594 -0.0807 0.0756 1.0000
11.750 1.5037 0.04813 0.04007 -0.0786 0.0680 1.0000
12.000 1.4870 0.05261 0.04467 -0.0773 0.0640 1.0000
12.250 1.4756 0.05682 0.04905 -0.0765 0.0599 1.0000
12.500 1.4653 0.06108 0.05348 -0.0761 0.0563 1.0000
12.750 1.4532 0.06575 0.05826 -0.0762 0.0538 1.0000
13.000 1.4402 0.07063 0.06323 -0.0764 0.0520 1.0000
13.250 1.4328 0.07493 0.06770 -0.0766 0.0496 1.0000
13.500 1.4252 0.07931 0.07223 -0.0770 0.0476 1.0000
13.750 1.4183 0.08361 0.07661 -0.0773 0.0459 1.0000
14.000 1.4133 0.08746 0.08051 -0.0773 0.0445 1.0000
14.250 1.4170 0.08940 0.08235 -0.0754 0.0428 1.0000
14.500 1.4266 0.09082 0.08389 -0.0733 0.0415 1.0000
14.750 1.4365 0.09242 0.08559 -0.0713 0.0402 1.0000
15.000 1.4422 0.09486 0.08815 -0.0702 0.0388 1.0000
15.250 1.4456 0.09773 0.09113 -0.0696 0.0375 1.0000
15.500 1.4502 0.10042 0.09386 -0.0689 0.0362 1.0000
15.750 1.4604 0.10260 0.09612 -0.0671 0.0353 1.0000
16.000 1.4636 0.10620 0.09995 -0.0665 0.0350 1.0000
16.250 1.4585 0.11096 0.10495 -0.0673 0.0350 1.0000
16.500 1.4477 0.11654 0.11079 -0.0694 0.0350 1.0000
16.750 1.4340 0.12275 0.11726 -0.0725 0.0352 1.0000
17.000 1.4171 0.12983 0.12462 -0.0767 0.0354 1.0000
17.250 1.3958 0.13827 0.13337 -0.0823 0.0358 1.0000
17.500 1.3697 0.14855 0.14396 -0.0896 0.0365 1.0000
17.750 1.3300 0.16338 0.15910 -0.1010 0.0376 1.0000
18.000 1.2739 0.18580 0.18175 -0.1179 0.0402 1.0000
18.250 1.2508 0.19996 0.19591 -0.1271 0.0421 1.0000
18.500 1.2438 0.20887 0.20480 -0.1322 0.0428 1.0000
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Polar data table (+)
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