GOE 530 AIRFOIL (goe530-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 530 AIRFOIL (goe530-il) Reynolds number: 50,000 Max Cl/Cd: 32.13 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe530-il-50000-n5.txt Download as CSV file: xf-goe530-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 530 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2879 0.11108 0.10442 -0.0275 1.0000 0.1396
-8.500 -0.3013 0.11014 0.10359 -0.0253 1.0000 0.1419
-8.250 -0.3162 0.10896 0.10246 -0.0322 0.9895 0.1469
-8.000 -0.2975 0.10424 0.09775 -0.0347 0.9832 0.1494
-7.750 -0.2703 0.10029 0.09379 -0.0355 0.9779 0.1538
-7.500 -0.2588 0.09719 0.09068 -0.0393 0.9694 0.1588
-7.250 -0.2799 0.09590 0.08936 -0.0481 0.9515 0.1644
-7.000 -0.2648 0.09159 0.08506 -0.0492 0.9438 0.1658
-6.750 -0.2384 0.08746 0.08094 -0.0501 0.9393 0.1682
-6.500 -0.2256 0.08456 0.07803 -0.0508 0.9304 0.1713
-6.000 -0.2194 0.07139 0.06425 -0.0640 0.9077 0.1045
-5.750 -0.1955 0.06769 0.06040 -0.0667 0.9023 0.1005
-5.500 -0.1899 0.06509 0.05772 -0.0658 0.8911 0.0988
-5.250 -0.1668 0.06119 0.05358 -0.0686 0.8851 0.0968
-5.000 -0.1609 0.05883 0.05104 -0.0672 0.8734 0.0971
-4.750 -0.1345 0.05550 0.04742 -0.0693 0.8672 0.0978
-4.500 -0.1272 0.05336 0.04507 -0.0673 0.8553 0.0978
-4.250 -0.0994 0.05020 0.04156 -0.0687 0.8491 0.0974
-4.000 -0.0909 0.04834 0.03944 -0.0662 0.8373 0.0973
-3.750 -0.0625 0.04585 0.03657 -0.0669 0.8312 0.0990
-3.500 -0.0523 0.04437 0.03479 -0.0643 0.8199 0.1004
-3.250 -0.0240 0.04219 0.03213 -0.0644 0.8136 0.1018
-3.000 -0.0098 0.04085 0.03044 -0.0621 0.8032 0.1024
-2.750 0.0189 0.03928 0.02866 -0.0621 0.7964 0.1047
-2.500 0.0398 0.03839 0.02769 -0.0610 0.7873 0.1072
-2.000 0.1005 0.03586 0.02462 -0.0609 0.7732 0.1121
-1.750 0.1191 0.03521 0.02369 -0.0591 0.7621 0.1151
-1.500 0.1588 0.03392 0.02223 -0.0605 0.7569 0.1189
-1.250 0.1766 0.03351 0.02175 -0.0587 0.7450 0.1212
-1.000 0.2166 0.03252 0.02061 -0.0601 0.7391 0.1269
-0.750 0.2429 0.03217 0.02003 -0.0595 0.7279 0.1313
-0.500 0.2923 0.03118 0.01903 -0.0628 0.7213 0.1373
-0.250 0.3224 0.03087 0.01863 -0.0629 0.7107 0.1443
0.000 0.3626 0.03013 0.01786 -0.0644 0.7027 0.1517
0.250 0.3889 0.02989 0.01760 -0.0638 0.6918 0.1608
0.500 0.4243 0.02927 0.01700 -0.0644 0.6833 0.1732
0.750 0.4465 0.02913 0.01689 -0.0632 0.6714 0.1863
1.000 0.4818 0.02839 0.01628 -0.0637 0.6632 0.2184
1.250 0.4997 0.02798 0.01636 -0.0620 0.6506 0.2958
1.750 0.6734 0.02596 0.01534 -0.0828 0.6269 1.0000
2.000 0.6914 0.02625 0.01549 -0.0808 0.6137 1.0000
2.250 0.7170 0.02623 0.01529 -0.0797 0.6027 1.0000
2.500 0.7368 0.02644 0.01538 -0.0779 0.5898 1.0000
2.750 0.7542 0.02677 0.01561 -0.0759 0.5769 1.0000
3.000 0.7784 0.02683 0.01552 -0.0747 0.5659 1.0000
3.250 0.7974 0.02712 0.01571 -0.0728 0.5537 1.0000
3.500 0.8145 0.02750 0.01602 -0.0708 0.5415 1.0000
3.750 0.8396 0.02757 0.01594 -0.0698 0.5313 1.0000
4.000 0.8551 0.02804 0.01636 -0.0676 0.5192 1.0000
4.250 0.8738 0.02842 0.01668 -0.0658 0.5083 1.0000
4.500 0.8973 0.02861 0.01676 -0.0647 0.4985 1.0000
4.750 0.9114 0.02921 0.01733 -0.0624 0.4872 1.0000
5.000 0.9371 0.02936 0.01735 -0.0616 0.4781 1.0000
5.250 0.9495 0.03007 0.01807 -0.0592 0.4674 1.0000
5.500 0.9726 0.03039 0.01829 -0.0581 0.4585 1.0000
5.750 0.9867 0.03106 0.01897 -0.0559 0.4484 1.0000
6.000 1.0090 0.03148 0.01932 -0.0548 0.4400 1.0000
6.250 1.0215 0.03227 0.02013 -0.0525 0.4307 1.0000
6.500 1.0479 0.03261 0.02036 -0.0520 0.4234 1.0000
6.750 1.0542 0.03367 0.02153 -0.0490 0.4144 1.0000
7.000 1.0793 0.03406 0.02185 -0.0484 0.4072 1.0000
7.250 1.0863 0.03515 0.02302 -0.0455 0.3992 1.0000
7.500 1.1017 0.03593 0.02381 -0.0437 0.3921 1.0000
7.750 1.1267 0.03645 0.02430 -0.0432 0.3861 1.0000
8.000 1.1248 0.03797 0.02598 -0.0395 0.3792 1.0000
8.250 1.1405 0.03882 0.02685 -0.0379 0.3733 1.0000
8.500 1.1663 0.03935 0.02734 -0.0375 0.3682 1.0000
8.750 1.1506 0.04130 0.02949 -0.0322 0.3621 1.0000
9.000 1.1577 0.04248 0.03073 -0.0297 0.3565 1.0000
9.250 1.1867 0.04288 0.03112 -0.0297 0.3521 1.0000
9.500 1.1690 0.04529 0.03369 -0.0250 0.3471 1.0000
9.750 1.1504 0.04813 0.03669 -0.0211 0.3419 1.0000
10.000 1.1589 0.04960 0.03823 -0.0195 0.3377 1.0000
10.250 1.1936 0.04955 0.03819 -0.0196 0.3342 1.0000
10.500 1.0851 0.06008 0.04898 -0.0137 0.3258 1.0000
10.750 1.0737 0.06386 0.05285 -0.0126 0.3204 1.0000
11.000 1.1092 0.06282 0.05186 -0.0116 0.3178 1.0000
11.250 0.9638 0.08464 0.07381 -0.0153 0.3030 1.0000
11.500 0.9845 0.08488 0.07410 -0.0141 0.3007 1.0000
12.000 0.9267 0.10073 0.09008 -0.0177 0.2856 1.0000
12.250 0.9616 0.09854 0.08795 -0.0155 0.2831 1.0000
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Polar data table (+)
Polar graphs
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