GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 532 AIRFOIL (goe532-il) Reynolds number: 50,000 Max Cl/Cd: 34.68 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe532-il-50000-n5.txt Download as CSV file: xf-goe532-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 532 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2565 0.10042 0.09380 -0.0307 1.0000 0.1637
-8.000 -0.2601 0.09842 0.09192 -0.0296 1.0000 0.1657
-7.500 -0.3414 0.09229 0.08617 -0.0329 1.0000 0.1103
-7.000 -0.3220 0.07961 0.07339 -0.0440 0.9853 0.0829
-6.750 -0.2954 0.07458 0.06831 -0.0505 0.9728 0.0819
-6.500 -0.2700 0.06859 0.06220 -0.0591 0.9590 0.0812
-6.250 -0.2445 0.06264 0.05607 -0.0671 0.9448 0.0802
-6.000 -0.2186 0.05679 0.04995 -0.0744 0.9305 0.0785
-5.750 -0.1907 0.05097 0.04371 -0.0813 0.9165 0.0769
-5.500 -0.1582 0.04583 0.03802 -0.0872 0.9043 0.0758
-5.250 -0.1217 0.04216 0.03390 -0.0916 0.8934 0.0765
-5.000 -0.0910 0.03947 0.03081 -0.0938 0.8792 0.0781
-4.750 -0.0582 0.03694 0.02783 -0.0959 0.8660 0.0793
-4.500 -0.0211 0.03455 0.02496 -0.0981 0.8551 0.0799
-4.250 0.0098 0.03275 0.02277 -0.0988 0.8405 0.0806
-4.000 0.0407 0.03126 0.02091 -0.0993 0.8263 0.0818
-3.750 0.0730 0.02997 0.01927 -0.0997 0.8132 0.0840
-3.500 0.1048 0.02877 0.01800 -0.1002 0.8009 0.0869
-3.250 0.1323 0.02789 0.01699 -0.0997 0.7860 0.0894
-3.000 0.1604 0.02709 0.01602 -0.0992 0.7722 0.0917
-2.750 0.1900 0.02634 0.01507 -0.0989 0.7600 0.0946
-2.500 0.2181 0.02567 0.01433 -0.0985 0.7475 0.0992
-2.250 0.2442 0.02520 0.01378 -0.0980 0.7344 0.1054
-2.000 0.2729 0.02470 0.01316 -0.0977 0.7234 0.1123
-1.750 0.3016 0.02425 0.01262 -0.0976 0.7126 0.1233
-1.500 0.3291 0.02377 0.01227 -0.0975 0.7015 0.1459
-1.250 0.3590 0.02273 0.01192 -0.0980 0.6930 0.2842
-1.000 0.3810 0.02230 0.01218 -0.0967 0.6823 0.4804
-0.750 0.4012 0.02183 0.01227 -0.0939 0.6750 0.6485
-0.500 0.4200 0.02131 0.01234 -0.0906 0.6657 0.8293
-0.250 0.4664 0.02122 0.01196 -0.0937 0.6581 1.0000
0.000 0.4928 0.02162 0.01209 -0.0938 0.6491 1.0000
0.250 0.5221 0.02191 0.01208 -0.0940 0.6419 1.0000
0.500 0.5491 0.02231 0.01225 -0.0939 0.6345 1.0000
0.750 0.5758 0.02274 0.01249 -0.0938 0.6272 1.0000
1.000 0.6053 0.02305 0.01257 -0.0939 0.6217 1.0000
1.250 0.6291 0.02362 0.01305 -0.0935 0.6141 1.0000
1.500 0.6558 0.02404 0.01332 -0.0933 0.6073 1.0000
1.750 0.6839 0.02439 0.01349 -0.0931 0.6010 1.0000
2.000 0.7062 0.02499 0.01405 -0.0924 0.5924 1.0000
2.250 0.7351 0.02523 0.01411 -0.0922 0.5854 1.0000
2.500 0.7565 0.02581 0.01466 -0.0913 0.5758 1.0000
2.750 0.7845 0.02602 0.01473 -0.0908 0.5676 1.0000
3.000 0.8059 0.02655 0.01524 -0.0899 0.5578 1.0000
3.250 0.8339 0.02669 0.01525 -0.0893 0.5490 1.0000
3.500 0.8542 0.02720 0.01575 -0.0882 0.5379 1.0000
3.750 0.8833 0.02723 0.01562 -0.0877 0.5293 1.0000
4.000 0.9017 0.02784 0.01631 -0.0864 0.5183 1.0000
4.250 0.9299 0.02801 0.01636 -0.0859 0.5111 1.0000
4.500 0.9479 0.02875 0.01720 -0.0847 0.5016 1.0000
4.750 0.9758 0.02891 0.01730 -0.0843 0.4944 1.0000
5.000 0.9929 0.02967 0.01816 -0.0829 0.4844 1.0000
5.250 1.0205 0.02981 0.01823 -0.0824 0.4767 1.0000
5.500 1.0364 0.03060 0.01915 -0.0809 0.4663 1.0000
5.750 1.0644 0.03069 0.01919 -0.0803 0.4586 1.0000
6.000 1.0784 0.03157 0.02022 -0.0787 0.4474 1.0000
6.250 1.1019 0.03190 0.02055 -0.0777 0.4385 1.0000
6.500 1.1192 0.03255 0.02130 -0.0763 0.4275 1.0000
6.750 1.1364 0.03321 0.02204 -0.0748 0.4168 1.0000
7.000 1.1599 0.03345 0.02228 -0.0738 0.4070 1.0000
7.250 1.1710 0.03441 0.02338 -0.0718 0.3942 1.0000
7.500 1.1857 0.03510 0.02413 -0.0701 0.3821 1.0000
7.750 1.2045 0.03544 0.02446 -0.0686 0.3707 1.0000
8.000 1.2144 0.03634 0.02543 -0.0664 0.3579 1.0000
8.250 1.2219 0.03739 0.02657 -0.0642 0.3455 1.0000
8.500 1.2319 0.03820 0.02739 -0.0620 0.3347 1.0000
8.750 1.2432 0.03893 0.02811 -0.0600 0.3247 1.0000
9.000 1.2454 0.04046 0.02973 -0.0576 0.3149 1.0000
9.250 1.2608 0.04111 0.03036 -0.0561 0.3073 1.0000
9.500 1.2610 0.04303 0.03240 -0.0541 0.2988 1.0000
9.750 1.2753 0.04381 0.03314 -0.0527 0.2916 1.0000
10.000 1.2739 0.04601 0.03546 -0.0511 0.2836 1.0000
10.250 1.2871 0.04688 0.03628 -0.0498 0.2764 1.0000
10.500 1.2837 0.04947 0.03903 -0.0486 0.2690 1.0000
10.750 1.3014 0.05005 0.03953 -0.0475 0.2624 1.0000
11.000 1.2925 0.05347 0.04316 -0.0467 0.2559 1.0000
11.250 1.3069 0.05431 0.04395 -0.0457 0.2486 1.0000
11.500 1.2970 0.05801 0.04781 -0.0453 0.2416 1.0000
11.750 1.3081 0.05929 0.04908 -0.0445 0.2344 1.0000
12.000 1.3021 0.06287 0.05283 -0.0444 0.2283 1.0000
12.250 1.3023 0.06568 0.05574 -0.0442 0.2216 1.0000
12.500 1.3074 0.06791 0.05801 -0.0438 0.2150 1.0000
12.750 1.2937 0.07279 0.06308 -0.0446 0.2081 1.0000
13.000 1.3117 0.07323 0.06344 -0.0435 0.2010 1.0000
13.250 1.2807 0.08090 0.07142 -0.0458 0.1943 1.0000
13.500 1.3076 0.07993 0.07035 -0.0440 0.1872 1.0000
13.750 1.2631 0.09026 0.08099 -0.0478 0.1808 1.0000
14.000 1.2522 0.09552 0.08637 -0.0493 0.1742 1.0000
14.250 1.2684 0.09619 0.08702 -0.0484 0.1686 1.0000
14.500 1.1581 0.12113 0.11229 -0.0610 0.1587 1.0000
14.750 1.1893 0.11850 0.10967 -0.0584 0.1557 1.0000
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Polar data table (+)
Polar graphs
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