GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 612 AIRFOIL (goe612-il) Reynolds number: 100,000 Max Cl/Cd: 51.32 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe612-il-100000.txt Download as CSV file: xf-goe612-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 612 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2144 0.10292 0.09827 -0.0536 0.9661 0.1529
-8.000 -0.2528 0.10137 0.09679 -0.0638 0.9530 0.1604
-7.750 -0.2215 0.09660 0.09202 -0.0625 0.9487 0.1625
-7.500 -0.1853 0.09365 0.08902 -0.0625 0.9447 0.1672
-7.250 -0.1919 0.09145 0.08685 -0.0667 0.9355 0.1750
-7.000 -0.2110 0.08810 0.08354 -0.0706 0.9248 0.1786
-6.750 -0.1662 0.08485 0.08025 -0.0708 0.9238 0.1823
-6.500 -0.1758 0.08370 0.07914 -0.0680 0.9126 0.1855
-6.000 -0.3093 0.04787 0.04123 -0.0902 0.8847 0.1029
-5.750 -0.2964 0.04525 0.03832 -0.0894 0.8788 0.1025
-5.500 -0.2717 0.04221 0.03488 -0.0905 0.8749 0.1036
-5.250 -0.2492 0.04083 0.03350 -0.0905 0.8702 0.1056
-5.000 -0.2406 0.03980 0.03229 -0.0881 0.8631 0.1067
-4.750 -0.2143 0.03824 0.03043 -0.0884 0.8591 0.1084
-4.500 -0.1790 0.03660 0.02840 -0.0899 0.8562 0.1109
-4.250 -0.1749 0.03616 0.02773 -0.0864 0.8486 0.1127
-4.000 -0.1513 0.03531 0.02652 -0.0859 0.8438 0.1164
-3.750 -0.1184 0.03443 0.02569 -0.0870 0.8405 0.1220
-3.500 -0.0871 0.03377 0.02479 -0.0874 0.8368 0.1283
-3.250 -0.0824 0.03363 0.02462 -0.0841 0.8291 0.1320
-3.000 -0.0535 0.03323 0.02420 -0.0843 0.8250 0.1424
-2.750 -0.0153 0.03249 0.02351 -0.0858 0.8220 0.1578
-2.500 -0.0108 0.03269 0.02380 -0.0826 0.8145 0.1683
-2.250 0.0129 0.03252 0.02366 -0.0820 0.8092 0.1915
-2.000 0.0491 0.03212 0.02342 -0.0831 0.8055 0.2258
-1.750 0.0610 0.03243 0.02381 -0.0808 0.7979 0.2486
-1.500 0.0921 0.03219 0.02369 -0.0810 0.7906 0.2843
-1.250 0.1493 0.03123 0.02290 -0.0844 0.7864 0.3403
-1.000 0.1534 0.03163 0.02341 -0.0806 0.7739 0.3660
-0.750 0.2040 0.03072 0.02262 -0.0830 0.7699 0.4195
-0.500 0.2050 0.03147 0.02343 -0.0792 0.7590 0.4409
-0.250 0.2450 0.03090 0.02293 -0.0803 0.7545 0.4805
0.000 0.2957 0.02987 0.02198 -0.0829 0.7519 0.5253
0.250 0.2929 0.03079 0.02301 -0.0786 0.7396 0.5463
0.500 0.3432 0.02968 0.02209 -0.0811 0.7362 0.6003
0.750 0.4033 0.02782 0.02091 -0.0846 0.7346 0.7302
1.000 0.4899 0.02748 0.02076 -0.0959 0.7267 1.0000
1.250 0.5327 0.02696 0.02003 -0.0977 0.7211 1.0000
1.500 0.5891 0.02587 0.01875 -0.1011 0.7183 1.0000
1.750 0.6438 0.02485 0.01755 -0.1043 0.7154 1.0000
2.000 0.6469 0.02556 0.01821 -0.1002 0.7023 1.0000
2.250 0.7037 0.02437 0.01688 -0.1036 0.6988 1.0000
2.500 0.7111 0.02491 0.01739 -0.1001 0.6860 1.0000
2.750 0.7655 0.02379 0.01614 -0.1031 0.6814 1.0000
3.000 0.7789 0.02407 0.01638 -0.1003 0.6687 1.0000
3.250 0.8332 0.02295 0.01513 -0.1034 0.6629 1.0000
3.500 0.8475 0.02312 0.01528 -0.1007 0.6492 1.0000
3.750 0.8760 0.02285 0.01495 -0.1000 0.6375 1.0000
4.000 0.9195 0.02208 0.01404 -0.1015 0.6275 1.0000
4.250 0.9392 0.02203 0.01395 -0.0995 0.6125 1.0000
4.500 0.9626 0.02188 0.01375 -0.0981 0.5973 1.0000
4.750 0.9874 0.02171 0.01350 -0.0969 0.5818 1.0000
5.000 1.0120 0.02157 0.01327 -0.0957 0.5657 1.0000
5.250 1.0354 0.02151 0.01311 -0.0944 0.5492 1.0000
5.500 1.0579 0.02154 0.01305 -0.0930 0.5327 1.0000
5.750 1.0799 0.02165 0.01304 -0.0916 0.5167 1.0000
6.000 1.1020 0.02183 0.01309 -0.0903 0.5013 1.0000
6.250 1.1249 0.02205 0.01318 -0.0891 0.4867 1.0000
6.500 1.1469 0.02235 0.01335 -0.0879 0.4726 1.0000
6.750 1.1632 0.02282 0.01376 -0.0859 0.4587 1.0000
7.000 1.1814 0.02331 0.01418 -0.0843 0.4458 1.0000
7.250 1.2035 0.02378 0.01454 -0.0832 0.4340 1.0000
7.500 1.2267 0.02427 0.01490 -0.0825 0.4225 1.0000
7.750 1.2416 0.02493 0.01558 -0.0804 0.4115 1.0000
8.000 1.2659 0.02552 0.01606 -0.0799 0.4014 1.0000
8.250 1.2837 0.02617 0.01669 -0.0784 0.3912 1.0000
8.500 1.3030 0.02690 0.01741 -0.0772 0.3819 1.0000
8.750 1.3266 0.02757 0.01800 -0.0767 0.3725 1.0000
9.000 1.3408 0.02841 0.01889 -0.0747 0.3636 1.0000
9.250 1.3681 0.02910 0.01945 -0.0748 0.3543 1.0000
9.500 1.3763 0.03002 0.02049 -0.0720 0.3460 1.0000
9.750 1.4050 0.03076 0.02110 -0.0723 0.3369 1.0000
10.000 1.4096 0.03175 0.02225 -0.0690 0.3293 1.0000
10.250 1.4339 0.03256 0.02299 -0.0688 0.3209 1.0000
10.500 1.4430 0.03364 0.02417 -0.0662 0.3137 1.0000
10.750 1.4545 0.03456 0.02514 -0.0640 0.3062 1.0000
11.000 1.4779 0.03560 0.02614 -0.0638 0.2987 1.0000
11.250 1.4740 0.03672 0.02745 -0.0594 0.2923 1.0000
11.500 1.5182 0.03755 0.02806 -0.0623 0.2841 1.0000
11.750 1.5003 0.03891 0.02971 -0.0561 0.2792 1.0000
12.000 1.5037 0.04011 0.03104 -0.0532 0.2735 1.0000
12.250 1.5464 0.04098 0.03173 -0.0556 0.2669 1.0000
12.500 1.5276 0.04273 0.03379 -0.0501 0.2629 1.0000
12.750 1.5241 0.04435 0.03558 -0.0468 0.2584 1.0000
13.000 1.5479 0.04520 0.03641 -0.0466 0.2534 1.0000
13.250 1.5596 0.04678 0.03806 -0.0453 0.2491 1.0000
13.500 1.5385 0.04921 0.04078 -0.0408 0.2458 1.0000
13.750 1.5288 0.05144 0.04320 -0.0379 0.2421 1.0000
14.000 1.5403 0.05283 0.04465 -0.0367 0.2385 1.0000
14.250 1.5819 0.05354 0.04527 -0.0382 0.2345 1.0000
14.500 1.5385 0.05763 0.04972 -0.0332 0.2328 1.0000
14.750 1.4856 0.06327 0.05571 -0.0293 0.2309 1.0000
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Polar data table (+)
Polar graphs
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