GOE 566 AIRFOIL (goe566-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 566 AIRFOIL (goe566-il) Reynolds number: 100,000 Max Cl/Cd: 52.36 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe566-il-100000.txt Download as CSV file: xf-goe566-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 566 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4263 0.09607 0.09100 -0.0265 1.0000 0.1037
-8.500 -0.4488 0.09412 0.08921 -0.0315 1.0000 0.1056
-8.250 -0.4708 0.09154 0.08670 -0.0368 1.0000 0.1061
-8.000 -0.4302 0.08615 0.08128 -0.0285 1.0000 0.1110
-7.750 -0.4323 0.08343 0.07863 -0.0283 1.0000 0.1147
-7.500 -0.4458 0.08052 0.07581 -0.0311 1.0000 0.1186
-7.250 -0.4791 0.07892 0.07405 -0.0383 1.0000 0.1211
-7.000 -0.4566 0.07349 0.06886 -0.0328 1.0000 0.1238
-6.750 -0.4510 0.07102 0.06644 -0.0304 1.0000 0.1279
-6.500 -0.4757 0.07001 0.06506 -0.0346 1.0000 0.1359
-6.250 -0.4635 0.06501 0.06036 -0.0306 1.0000 0.1386
-6.000 -0.4582 0.06290 0.05831 -0.0277 1.0000 0.1451
-5.750 -0.4622 0.05979 0.05506 -0.0281 1.0000 0.1534
-5.500 -0.4556 0.05752 0.05282 -0.0254 1.0000 0.1593
-5.250 -0.4531 0.05456 0.04971 -0.0252 1.0000 0.1692
-5.000 -0.4472 0.05242 0.04736 -0.0248 1.0000 0.1826
-4.750 -0.4375 0.05075 0.04557 -0.0234 1.0000 0.1957
-4.500 -0.4290 0.04719 0.04216 -0.0213 1.0000 0.2015
-4.250 -0.4192 0.04507 0.04000 -0.0198 1.0000 0.2181
-4.000 -0.4094 0.04318 0.03797 -0.0188 1.0000 0.2442
-3.750 -0.3568 0.03248 0.02503 -0.0230 1.0000 0.1077
-3.500 -0.3364 0.03012 0.02246 -0.0220 1.0000 0.1026
-3.250 -0.3153 0.02824 0.02022 -0.0210 1.0000 0.1020
-3.000 -0.2934 0.02643 0.01806 -0.0200 1.0000 0.1001
-2.750 -0.2712 0.02488 0.01615 -0.0190 1.0000 0.0982
-2.500 -0.2493 0.02369 0.01468 -0.0179 1.0000 0.0979
-2.250 -0.2281 0.02281 0.01361 -0.0169 1.0000 0.0994
-2.000 -0.1940 0.02218 0.01276 -0.0183 0.9960 0.1039
-1.750 -0.1550 0.02149 0.01189 -0.0205 0.9900 0.1066
-1.500 -0.1159 0.02068 0.01120 -0.0229 0.9843 0.1121
-1.250 -0.0796 0.02026 0.01075 -0.0247 0.9769 0.1204
-1.000 -0.0384 0.01979 0.01049 -0.0276 0.9703 0.1401
-0.750 0.0318 0.01625 0.00994 -0.0350 0.9710 1.0000
-0.500 0.0730 0.01652 0.00990 -0.0379 0.9604 1.0000
-0.250 0.1158 0.01682 0.00997 -0.0411 0.9508 1.0000
0.000 0.1691 0.01702 0.00999 -0.0461 0.9413 1.0000
0.250 0.2170 0.01703 0.00986 -0.0498 0.9279 1.0000
0.500 0.2727 0.01680 0.00954 -0.0546 0.9138 1.0000
0.750 0.3222 0.01660 0.00928 -0.0583 0.9014 1.0000
1.000 0.3694 0.01642 0.00907 -0.0616 0.8921 1.0000
1.250 0.4129 0.01622 0.00885 -0.0641 0.8823 1.0000
1.500 0.4449 0.01614 0.00877 -0.0644 0.8698 1.0000
1.750 0.4778 0.01600 0.00864 -0.0647 0.8572 1.0000
2.000 0.5103 0.01579 0.00845 -0.0648 0.8441 1.0000
2.250 0.5408 0.01556 0.00823 -0.0643 0.8298 1.0000
2.500 0.5692 0.01535 0.00805 -0.0634 0.8144 1.0000
2.750 0.5961 0.01513 0.00786 -0.0622 0.7977 1.0000
3.000 0.6231 0.01488 0.00762 -0.0609 0.7795 1.0000
3.250 0.6484 0.01462 0.00738 -0.0592 0.7575 1.0000
3.500 0.6738 0.01434 0.00708 -0.0574 0.7318 1.0000
3.750 0.6964 0.01419 0.00689 -0.0553 0.6993 1.0000
4.000 0.7190 0.01412 0.00674 -0.0532 0.6597 1.0000
4.250 0.7405 0.01422 0.00667 -0.0510 0.6107 1.0000
4.500 0.7603 0.01452 0.00672 -0.0487 0.5535 1.0000
4.750 0.7797 0.01501 0.00691 -0.0466 0.5004 1.0000
5.000 0.8001 0.01564 0.00724 -0.0450 0.4608 1.0000
5.250 0.8213 0.01631 0.00772 -0.0436 0.4303 1.0000
5.500 0.8433 0.01698 0.00823 -0.0425 0.4059 1.0000
5.750 0.8660 0.01763 0.00883 -0.0416 0.3858 1.0000
6.000 0.8888 0.01826 0.00945 -0.0406 0.3675 1.0000
6.250 0.9108 0.01886 0.01004 -0.0396 0.3485 1.0000
6.500 0.9317 0.01944 0.01059 -0.0384 0.3285 1.0000
6.750 0.9513 0.01995 0.01115 -0.0370 0.3065 1.0000
7.000 0.9701 0.02051 0.01167 -0.0355 0.2840 1.0000
7.250 0.9878 0.02105 0.01228 -0.0338 0.2595 1.0000
7.500 1.0041 0.02164 0.01291 -0.0320 0.2319 1.0000
7.750 1.0182 0.02230 0.01357 -0.0298 0.1997 1.0000
8.000 1.0295 0.02305 0.01421 -0.0273 0.1559 1.0000
8.250 1.0380 0.02468 0.01544 -0.0245 0.1166 1.0000
8.500 1.0500 0.02655 0.01722 -0.0222 0.0976 1.0000
8.750 1.0653 0.02854 0.01912 -0.0205 0.0867 1.0000
9.000 1.0844 0.03052 0.02101 -0.0194 0.0784 1.0000
9.250 1.1040 0.03247 0.02315 -0.0181 0.0718 1.0000
9.500 1.1248 0.03446 0.02520 -0.0173 0.0670 1.0000
9.750 1.1479 0.03744 0.02828 -0.0169 0.0635 1.0000
10.000 1.1616 0.03934 0.03058 -0.0149 0.0603 1.0000
10.250 1.1763 0.04151 0.03299 -0.0134 0.0574 1.0000
10.500 1.1898 0.04417 0.03589 -0.0118 0.0558 1.0000
10.750 1.2009 0.04729 0.03923 -0.0103 0.0547 1.0000
11.000 1.2082 0.05149 0.04367 -0.0088 0.0537 1.0000
11.250 1.2033 0.05495 0.04752 -0.0059 0.0532 1.0000
11.500 1.1927 0.05780 0.05076 -0.0025 0.0528 1.0000
11.750 1.1771 0.06080 0.05406 0.0011 0.0526 1.0000
12.000 1.1595 0.06413 0.05766 0.0040 0.0525 1.0000
12.250 1.1406 0.06780 0.06157 0.0058 0.0526 1.0000
12.500 1.1191 0.07205 0.06604 0.0066 0.0527 1.0000
12.750 1.0991 0.07691 0.07108 0.0064 0.0529 1.0000
13.000 1.0779 0.08246 0.07678 0.0051 0.0532 1.0000
13.250 0.7581 0.12191 0.11712 -0.0212 0.0744 1.0000
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Polar data table (+)
Polar graphs
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