GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 533 AIRFOIL (goe533-il) Reynolds number: 200,000 Max Cl/Cd: 73.76 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe533-il-200000.txt Download as CSV file: xf-goe533-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 533 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2598 0.10463 0.10106 -0.0401 1.0000 0.0612
-9.750 -0.2647 0.10166 0.09815 -0.0417 1.0000 0.0635
-9.500 -0.3036 0.09786 0.09449 -0.0484 1.0000 0.0648
-9.250 -0.2898 0.09443 0.09109 -0.0453 1.0000 0.0656
-9.000 -0.2794 0.09258 0.08929 -0.0427 1.0000 0.0664
-8.750 -0.2773 0.09096 0.08774 -0.0405 1.0000 0.0673
-8.000 -0.2485 0.07591 0.07279 -0.0624 0.9728 0.0763
-7.750 -0.2148 0.07369 0.07055 -0.0631 0.9645 0.0784
-7.500 -0.2109 0.05878 0.05520 -0.0975 0.9307 0.0869
-7.250 -0.1734 0.05638 0.05299 -0.0962 0.9205 0.0884
-7.000 -0.1424 0.05443 0.05103 -0.0972 0.9009 0.0906
-6.750 -0.1424 0.04779 0.04362 -0.1084 0.8680 0.1003
-6.500 -0.1195 0.04492 0.04086 -0.1078 0.8482 0.1020
-6.250 -0.0986 0.04338 0.03927 -0.1071 0.8291 0.1048
-6.000 -0.0881 0.04022 0.03550 -0.1098 0.8110 0.1157
-5.750 -0.0672 0.03805 0.03338 -0.1093 0.7969 0.1181
-5.500 -0.0464 0.03634 0.03152 -0.1092 0.7844 0.1225
-5.000 -0.0018 0.02295 0.01562 -0.1100 0.7645 0.0658
-4.750 0.0244 0.02186 0.01423 -0.1095 0.7543 0.0653
-4.500 0.0510 0.02101 0.01314 -0.1090 0.7444 0.0648
-4.250 0.0774 0.01977 0.01169 -0.1086 0.7357 0.0646
-4.000 0.1039 0.01886 0.01062 -0.1082 0.7265 0.0648
-3.750 0.1306 0.01794 0.00954 -0.1078 0.7184 0.0652
-3.500 0.1566 0.01702 0.00861 -0.1074 0.7099 0.0665
-3.250 0.1832 0.01651 0.00807 -0.1070 0.7020 0.0686
-3.000 0.2098 0.01606 0.00760 -0.1066 0.6942 0.0704
-2.750 0.2365 0.01563 0.00711 -0.1061 0.6864 0.0721
-2.500 0.2633 0.01530 0.00671 -0.1057 0.6792 0.0740
-2.250 0.2895 0.01485 0.00629 -0.1053 0.6713 0.0770
-2.000 0.3169 0.01464 0.00602 -0.1051 0.6646 0.0821
-1.750 0.3433 0.01437 0.00579 -0.1047 0.6564 0.0900
-1.500 0.3707 0.01409 0.00550 -0.1045 0.6494 0.1070
-1.250 0.3930 0.01266 0.00541 -0.1043 0.6426 0.4625
-1.000 0.4178 0.01255 0.00554 -0.1033 0.6350 0.5637
-0.750 0.4439 0.01266 0.00568 -0.1025 0.6284 0.6172
-0.500 0.4693 0.01273 0.00580 -0.1017 0.6200 0.6528
-0.250 0.4953 0.01284 0.00587 -0.1009 0.6133 0.6879
0.000 0.5197 0.01290 0.00601 -0.0998 0.6056 0.7214
0.250 0.5437 0.01289 0.00605 -0.0985 0.5984 0.7556
0.500 0.5678 0.01288 0.00607 -0.0973 0.5916 0.7873
0.750 0.5916 0.01278 0.00605 -0.0962 0.5834 0.8126
1.000 0.6168 0.01272 0.00597 -0.0952 0.5770 0.8429
1.250 0.6418 0.01255 0.00597 -0.0942 0.5684 0.8910
1.500 0.6878 0.01251 0.00585 -0.0978 0.5609 1.0000
1.750 0.7163 0.01265 0.00593 -0.0983 0.5523 1.0000
2.000 0.7451 0.01276 0.00589 -0.0985 0.5446 1.0000
2.250 0.7724 0.01290 0.00597 -0.0985 0.5358 1.0000
2.500 0.8001 0.01300 0.00594 -0.0984 0.5278 1.0000
2.750 0.8269 0.01315 0.00604 -0.0982 0.5192 1.0000
3.000 0.8542 0.01329 0.00609 -0.0981 0.5119 1.0000
3.250 0.8810 0.01348 0.00624 -0.0979 0.5043 1.0000
3.500 0.9077 0.01363 0.00633 -0.0977 0.4967 1.0000
3.750 0.9346 0.01384 0.00647 -0.0975 0.4898 1.0000
4.000 0.9607 0.01403 0.00664 -0.0971 0.4820 1.0000
4.250 0.9880 0.01427 0.00676 -0.0970 0.4759 1.0000
4.500 1.0134 0.01448 0.00703 -0.0966 0.4683 1.0000
4.750 1.0400 0.01470 0.00717 -0.0964 0.4618 1.0000
5.000 1.0654 0.01495 0.00743 -0.0959 0.4544 1.0000
5.250 1.0911 0.01517 0.00762 -0.0956 0.4473 1.0000
5.500 1.1170 0.01546 0.00787 -0.0953 0.4408 1.0000
5.750 1.1420 0.01572 0.00816 -0.0948 0.4340 1.0000
6.000 1.1685 0.01602 0.00840 -0.0946 0.4285 1.0000
6.250 1.1929 0.01633 0.00878 -0.0941 0.4222 1.0000
6.500 1.2179 0.01662 0.00908 -0.0936 0.4161 1.0000
6.750 1.2444 0.01698 0.00937 -0.0935 0.4107 1.0000
7.000 1.2672 0.01727 0.00979 -0.0927 0.4040 1.0000
7.250 1.2917 0.01755 0.01004 -0.0922 0.3972 1.0000
7.500 1.3144 0.01787 0.01042 -0.0914 0.3898 1.0000
7.750 1.3372 0.01813 0.01070 -0.0906 0.3822 1.0000
8.000 1.3598 0.01847 0.01106 -0.0898 0.3748 1.0000
8.250 1.3811 0.01875 0.01140 -0.0888 0.3670 1.0000
8.500 1.4031 0.01912 0.01177 -0.0880 0.3596 1.0000
8.750 1.4231 0.01944 0.01218 -0.0868 0.3517 1.0000
9.000 1.4443 0.01983 0.01257 -0.0858 0.3444 1.0000
9.250 1.4622 0.02018 0.01303 -0.0843 0.3357 1.0000
9.500 1.4806 0.02059 0.01345 -0.0830 0.3274 1.0000
9.750 1.4968 0.02099 0.01391 -0.0813 0.3185 1.0000
10.000 1.5123 0.02145 0.01443 -0.0795 0.3097 1.0000
10.250 1.5263 0.02193 0.01493 -0.0775 0.3009 1.0000
10.500 1.5374 0.02244 0.01555 -0.0750 0.2924 1.0000
10.750 1.5479 0.02302 0.01611 -0.0725 0.2847 1.0000
11.000 1.5563 0.02365 0.01686 -0.0699 0.2758 1.0000
11.250 1.5644 0.02439 0.01757 -0.0673 0.2682 1.0000
11.500 1.5722 0.02517 0.01849 -0.0650 0.2598 1.0000
11.750 1.5784 0.02610 0.01941 -0.0626 0.2524 1.0000
12.000 1.5844 0.02709 0.02053 -0.0604 0.2439 1.0000
12.250 1.5883 0.02828 0.02175 -0.0582 0.2361 1.0000
12.500 1.5900 0.02968 0.02321 -0.0561 0.2267 1.0000
12.750 1.5907 0.03131 0.02489 -0.0543 0.2170 1.0000
13.000 1.5891 0.03325 0.02684 -0.0526 0.2082 1.0000
13.250 1.5873 0.03540 0.02904 -0.0513 0.1986 1.0000
13.500 1.5849 0.03776 0.03146 -0.0502 0.1897 1.0000
14.000 1.5744 0.04344 0.03721 -0.0487 0.1718 1.0000
14.250 1.5675 0.04666 0.04049 -0.0482 0.1628 1.0000
14.500 1.5566 0.05041 0.04423 -0.0480 0.1534 1.0000
14.750 1.5483 0.05416 0.04808 -0.0481 0.1416 1.0000
15.000 1.5383 0.05825 0.05224 -0.0484 0.1288 1.0000
15.250 1.5264 0.06274 0.05675 -0.0490 0.1159 1.0000
15.500 1.5127 0.06763 0.06162 -0.0498 0.1056 1.0000
15.750 1.4985 0.07275 0.06673 -0.0509 0.0987 1.0000
16.000 1.4839 0.07809 0.07206 -0.0521 0.0936 1.0000
16.250 1.4727 0.08305 0.07706 -0.0534 0.0892 1.0000
16.500 1.4621 0.08803 0.08208 -0.0547 0.0854 1.0000
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