GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 564 AIRFOIL (goe564-il) Reynolds number: 100,000 Max Cl/Cd: 52.55 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe564-il-100000-n5.txt Download as CSV file: xf-goe564-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 564 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4471 0.09149 0.08635 -0.0326 1.0000 0.0365
-8.750 -0.4527 0.08769 0.08263 -0.0335 1.0000 0.0362
-8.500 -0.4609 0.08398 0.07899 -0.0341 1.0000 0.0361
-8.250 -0.4732 0.08047 0.07558 -0.0344 1.0000 0.0359
-8.000 -0.4856 0.07657 0.07177 -0.0352 1.0000 0.0357
-7.750 -0.4953 0.07196 0.06721 -0.0370 1.0000 0.0356
-7.500 -0.5037 0.06702 0.06227 -0.0387 1.0000 0.0356
-7.250 -0.5096 0.06191 0.05710 -0.0400 1.0000 0.0361
-7.000 -0.5131 0.05655 0.05161 -0.0411 1.0000 0.0370
-6.750 -0.5154 0.05022 0.04502 -0.0419 1.0000 0.0381
-6.500 -0.5163 0.04286 0.03716 -0.0423 1.0000 0.0393
-6.250 -0.5118 0.03636 0.02988 -0.0418 1.0000 0.0404
-6.000 -0.4996 0.03306 0.02615 -0.0407 1.0000 0.0422
-5.750 -0.4827 0.03244 0.02550 -0.0396 1.0000 0.0446
-5.500 -0.4657 0.03032 0.02302 -0.0385 1.0000 0.0467
-5.250 -0.4473 0.02784 0.02003 -0.0375 1.0000 0.0488
-5.000 -0.4142 0.02557 0.01704 -0.0390 0.9962 0.0525
-4.750 -0.3821 0.02420 0.01552 -0.0404 0.9923 0.0548
-4.500 -0.3505 0.02309 0.01419 -0.0415 0.9886 0.0572
-4.250 -0.3177 0.02216 0.01301 -0.0427 0.9854 0.0611
-4.000 -0.2876 0.02121 0.01178 -0.0432 0.9813 0.0648
-3.750 -0.2559 0.02045 0.01099 -0.0442 0.9776 0.0679
-3.500 -0.2241 0.01980 0.01025 -0.0451 0.9738 0.0723
-3.250 -0.1942 0.01915 0.00948 -0.0456 0.9691 0.0779
-3.000 -0.1611 0.01869 0.00902 -0.0468 0.9652 0.0868
-2.750 -0.1314 0.01834 0.00866 -0.0473 0.9600 0.1006
-2.500 -0.1001 0.01804 0.00834 -0.0482 0.9549 0.1180
-2.250 -0.0653 0.01775 0.00801 -0.0497 0.9511 0.1340
-2.000 -0.0386 0.01751 0.00778 -0.0496 0.9442 0.1497
-1.750 -0.0060 0.01723 0.00760 -0.0508 0.9393 0.1734
-1.500 0.0262 0.01695 0.00737 -0.0518 0.9342 0.1941
-1.250 0.0548 0.01664 0.00717 -0.0520 0.9273 0.2164
-1.000 0.0904 0.01622 0.00696 -0.0537 0.9230 0.2626
-0.750 0.1177 0.01545 0.00689 -0.0539 0.9162 0.4415
-0.500 0.1960 0.01420 0.00703 -0.0633 0.9217 1.0000
-0.250 0.2229 0.01422 0.00692 -0.0630 0.9121 1.0000
0.000 0.2628 0.01416 0.00674 -0.0653 0.9073 1.0000
0.250 0.2912 0.01415 0.00664 -0.0653 0.8973 1.0000
0.500 0.3292 0.01402 0.00644 -0.0671 0.8894 1.0000
0.750 0.3672 0.01380 0.00616 -0.0686 0.8788 1.0000
1.000 0.4020 0.01357 0.00588 -0.0694 0.8647 1.0000
1.250 0.4372 0.01333 0.00558 -0.0702 0.8492 1.0000
1.500 0.4656 0.01319 0.00541 -0.0697 0.8296 1.0000
1.750 0.4961 0.01307 0.00525 -0.0697 0.8104 1.0000
2.000 0.5260 0.01301 0.00517 -0.0696 0.7925 1.0000
2.250 0.5542 0.01301 0.00516 -0.0693 0.7748 1.0000
2.500 0.5789 0.01305 0.00521 -0.0683 0.7531 1.0000
2.750 0.6057 0.01307 0.00521 -0.0676 0.7275 1.0000
3.000 0.6328 0.01309 0.00518 -0.0670 0.6967 1.0000
3.250 0.6611 0.01317 0.00514 -0.0665 0.6632 1.0000
3.500 0.6878 0.01335 0.00517 -0.0657 0.6261 1.0000
3.750 0.7116 0.01363 0.00532 -0.0646 0.5881 1.0000
4.000 0.7336 0.01396 0.00554 -0.0631 0.5460 1.0000
4.250 0.7540 0.01435 0.00576 -0.0614 0.4937 1.0000
4.500 0.7724 0.01488 0.00603 -0.0594 0.4330 1.0000
4.750 0.7898 0.01555 0.00638 -0.0574 0.3748 1.0000
5.000 0.8081 0.01620 0.00681 -0.0557 0.3307 1.0000
5.250 0.8274 0.01682 0.00728 -0.0541 0.2983 1.0000
5.500 0.8473 0.01742 0.00781 -0.0527 0.2752 1.0000
5.750 0.8677 0.01800 0.00835 -0.0514 0.2582 1.0000
6.250 0.9087 0.01915 0.00950 -0.0489 0.2283 1.0000
6.500 0.9290 0.01973 0.01013 -0.0476 0.2114 1.0000
6.750 0.9492 0.02030 0.01074 -0.0464 0.1939 1.0000
7.000 0.9693 0.02087 0.01138 -0.0451 0.1780 1.0000
7.250 0.9890 0.02144 0.01199 -0.0438 0.1591 1.0000
7.500 1.0087 0.02200 0.01258 -0.0426 0.1365 1.0000
7.750 1.0274 0.02267 0.01325 -0.0412 0.1114 1.0000
8.000 1.0429 0.02369 0.01408 -0.0395 0.0887 1.0000
8.250 1.0581 0.02487 0.01527 -0.0376 0.0691 1.0000
8.500 1.0733 0.02603 0.01645 -0.0358 0.0540 1.0000
8.750 1.0876 0.02722 0.01763 -0.0339 0.0454 1.0000
9.000 1.0996 0.02856 0.01899 -0.0317 0.0402 1.0000
9.250 1.1106 0.02992 0.02049 -0.0293 0.0367 1.0000
9.500 1.1175 0.03148 0.02215 -0.0265 0.0340 1.0000
9.750 1.1254 0.03301 0.02384 -0.0239 0.0314 1.0000
10.000 1.1337 0.03455 0.02556 -0.0213 0.0295 1.0000
10.250 1.1411 0.03625 0.02741 -0.0188 0.0281 1.0000
10.500 1.1475 0.03807 0.02935 -0.0165 0.0268 1.0000
10.750 1.1526 0.04014 0.03151 -0.0142 0.0257 1.0000
11.000 1.1576 0.04257 0.03409 -0.0122 0.0245 1.0000
11.250 1.1626 0.04461 0.03643 -0.0101 0.0236 1.0000
11.500 1.1646 0.04698 0.03908 -0.0080 0.0225 1.0000
11.750 1.1649 0.04963 0.04200 -0.0061 0.0220 1.0000
12.000 1.1619 0.05256 0.04520 -0.0044 0.0215 1.0000
12.250 1.1558 0.05579 0.04870 -0.0030 0.0211 1.0000
12.500 1.1470 0.05939 0.05256 -0.0021 0.0209 1.0000
12.750 1.1352 0.06344 0.05687 -0.0018 0.0207 1.0000
13.000 1.1216 0.06793 0.06161 -0.0022 0.0206 1.0000
13.250 1.1048 0.07318 0.06711 -0.0037 0.0205 1.0000
13.500 1.0855 0.07934 0.07350 -0.0064 0.0205 1.0000
13.750 1.0638 0.08656 0.08095 -0.0103 0.0207 1.0000
14.000 1.0385 0.09536 0.08997 -0.0159 0.0210 1.0000
14.250 1.0092 0.10636 0.10116 -0.0233 0.0214 1.0000
14.500 0.9760 0.11982 0.11476 -0.0321 0.0221 1.0000
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Polar data table (+)
Polar graphs
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