GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 564 AIRFOIL (goe564-il) Reynolds number: 100,000 Max Cl/Cd: 55.98 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe564-il-100000.txt Download as CSV file: xf-goe564-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4326 0.09893 0.09381 -0.0281 1.0000 0.1075
-8.500 -0.4534 0.09738 0.09241 -0.0308 1.0000 0.1090
-8.250 -0.4765 0.09549 0.09065 -0.0333 1.0000 0.1095
-8.000 -0.4632 0.09027 0.08546 -0.0298 1.0000 0.1115
-7.750 -0.4476 0.08691 0.08208 -0.0270 1.0000 0.1147
-7.500 -0.4532 0.08442 0.07966 -0.0259 1.0000 0.1171
-7.250 -0.4615 0.08155 0.07686 -0.0269 1.0000 0.1207
-7.000 -0.4935 0.07925 0.07442 -0.0361 1.0000 0.1245
-6.750 -0.4831 0.07423 0.06956 -0.0322 1.0000 0.1260
-6.500 -0.4749 0.07147 0.06686 -0.0284 1.0000 0.1285
-6.250 -0.4720 0.06889 0.06426 -0.0272 1.0000 0.1342
-6.000 -0.4771 0.06469 0.05987 -0.0313 1.0000 0.1409
-5.750 -0.4684 0.06225 0.05755 -0.0274 1.0000 0.1449
-5.500 -0.4648 0.05872 0.05371 -0.0306 1.0000 0.1557
-5.250 -0.4554 0.05565 0.05074 -0.0279 1.0000 0.1585
-5.000 -0.4454 0.05265 0.04746 -0.0292 1.0000 0.1710
-4.750 -0.4342 0.04986 0.04477 -0.0269 1.0000 0.1751
-4.500 -0.4222 0.04734 0.04214 -0.0263 1.0000 0.1897
-4.250 -0.3806 0.03249 0.02498 -0.0320 1.0000 0.0945
-4.000 -0.3598 0.02982 0.02188 -0.0311 1.0000 0.0944
-3.750 -0.3390 0.02774 0.01954 -0.0304 1.0000 0.0980
-3.500 -0.3171 0.02622 0.01781 -0.0295 1.0000 0.1005
-3.250 -0.2941 0.02469 0.01595 -0.0286 1.0000 0.1026
-3.000 -0.2711 0.02344 0.01438 -0.0276 1.0000 0.1064
-2.750 -0.2488 0.02241 0.01314 -0.0267 1.0000 0.1131
-2.500 -0.2267 0.02161 0.01223 -0.0257 1.0000 0.1198
-2.250 -0.2040 0.02065 0.01116 -0.0248 1.0000 0.1285
-2.000 -0.1821 0.01990 0.01040 -0.0238 1.0000 0.1433
-1.750 -0.1611 0.01936 0.00990 -0.0229 1.0000 0.1667
-1.500 -0.1405 0.01881 0.00946 -0.0219 1.0000 0.1899
-1.250 -0.1203 0.01854 0.00924 -0.0210 1.0000 0.2137
-1.000 -0.1011 0.01832 0.00921 -0.0200 1.0000 0.2418
-0.750 -0.0812 0.01813 0.00920 -0.0192 1.0000 0.2718
-0.500 -0.0405 0.01786 0.00939 -0.0223 0.9935 0.3444
-0.250 0.0202 0.01626 0.00952 -0.0283 0.9903 1.0000
0.000 0.0664 0.01687 0.00987 -0.0325 0.9812 1.0000
0.250 0.1125 0.01741 0.01022 -0.0366 0.9717 1.0000
0.500 0.1534 0.01778 0.01047 -0.0397 0.9606 1.0000
0.750 0.1943 0.01814 0.01073 -0.0426 0.9498 1.0000
1.000 0.2392 0.01841 0.01093 -0.0462 0.9386 1.0000
1.250 0.2888 0.01846 0.01094 -0.0503 0.9254 1.0000
1.500 0.3406 0.01823 0.01069 -0.0543 0.9099 1.0000
1.750 0.3926 0.01781 0.01028 -0.0580 0.8948 1.0000
2.000 0.4511 0.01729 0.00981 -0.0631 0.8856 1.0000
2.250 0.4907 0.01703 0.00960 -0.0647 0.8730 1.0000
2.500 0.5307 0.01671 0.00937 -0.0664 0.8604 1.0000
2.750 0.5709 0.01631 0.00904 -0.0678 0.8472 1.0000
3.000 0.6106 0.01585 0.00867 -0.0690 0.8326 1.0000
3.250 0.6496 0.01532 0.00825 -0.0698 0.8153 1.0000
3.500 0.6832 0.01491 0.00790 -0.0696 0.7940 1.0000
3.750 0.7145 0.01450 0.00754 -0.0689 0.7672 1.0000
4.000 0.7382 0.01428 0.00736 -0.0669 0.7315 1.0000
4.250 0.7647 0.01409 0.00712 -0.0653 0.6882 1.0000
4.500 0.7910 0.01413 0.00696 -0.0637 0.6345 1.0000
4.750 0.8106 0.01454 0.00708 -0.0612 0.5632 1.0000
5.000 0.8250 0.01518 0.00733 -0.0580 0.4777 1.0000
5.250 0.8404 0.01608 0.00773 -0.0553 0.4134 1.0000
5.500 0.8586 0.01697 0.00832 -0.0534 0.3718 1.0000
5.750 0.8785 0.01782 0.00897 -0.0519 0.3414 1.0000
6.000 0.8987 0.01859 0.00966 -0.0505 0.3145 1.0000
6.250 0.9183 0.01937 0.01035 -0.0490 0.2885 1.0000
6.500 0.9374 0.02018 0.01106 -0.0475 0.2637 1.0000
6.750 0.9558 0.02099 0.01178 -0.0460 0.2395 1.0000
7.000 0.9731 0.02172 0.01253 -0.0442 0.2142 1.0000
7.250 0.9897 0.02249 0.01334 -0.0423 0.1894 1.0000
7.500 1.0034 0.02320 0.01406 -0.0400 0.1590 1.0000
7.750 1.0142 0.02414 0.01485 -0.0371 0.1204 1.0000
8.000 1.0271 0.02577 0.01621 -0.0347 0.0974 1.0000
8.250 1.0442 0.02765 0.01801 -0.0330 0.0838 1.0000
8.500 1.0642 0.02943 0.01984 -0.0318 0.0749 1.0000
8.750 1.0877 0.03178 0.02233 -0.0310 0.0691 1.0000
9.000 1.1069 0.03344 0.02413 -0.0297 0.0636 1.0000
9.250 1.1295 0.03629 0.02701 -0.0292 0.0597 1.0000
9.500 1.1466 0.03878 0.02994 -0.0274 0.0578 1.0000
9.750 1.1599 0.04152 0.03311 -0.0253 0.0561 1.0000
10.000 1.1704 0.04407 0.03602 -0.0231 0.0542 1.0000
10.250 1.1823 0.04626 0.03833 -0.0213 0.0518 1.0000
10.500 1.1899 0.04951 0.04179 -0.0194 0.0506 1.0000
10.750 1.1900 0.05323 0.04588 -0.0166 0.0504 1.0000
11.000 1.1840 0.05680 0.04984 -0.0133 0.0505 1.0000
11.250 1.1688 0.06014 0.05359 -0.0091 0.0509 1.0000
11.500 1.1412 0.06363 0.05747 -0.0044 0.0516 1.0000
11.750 1.1004 0.06829 0.06255 -0.0011 0.0528 1.0000
12.000 1.0645 0.07382 0.06836 -0.0006 0.0535 1.0000
12.250 1.0262 0.08083 0.07560 -0.0029 0.0546 1.0000
12.500 0.9876 0.08977 0.08469 -0.0082 0.0559 1.0000
12.750 0.9532 0.10052 0.09552 -0.0153 0.0578 1.0000
13.000 0.9293 0.11094 0.10594 -0.0215 0.0591 1.0000
13.250 0.9225 0.11770 0.11268 -0.0240 0.0601 1.0000
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Polar data table (+)
Polar graphs
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