GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 50,000 Max Cl/Cd: 35.55 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe796-il-50000-n5.txt Download as CSV file: xf-goe796-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 796 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3673 0.10368 0.09617 -0.0441 1.0000 0.0663
-9.250 -0.3718 0.10019 0.09276 -0.0447 1.0000 0.0656
-9.000 -0.3787 0.09675 0.08942 -0.0450 1.0000 0.0651
-8.750 -0.3885 0.09341 0.08619 -0.0450 1.0000 0.0648
-8.500 -0.4017 0.09022 0.08312 -0.0447 1.0000 0.0645
-8.250 -0.4203 0.08719 0.08023 -0.0437 1.0000 0.0641
-8.000 -0.4419 0.08388 0.07705 -0.0430 1.0000 0.0637
-7.750 -0.4606 0.07994 0.07319 -0.0431 1.0000 0.0633
-7.500 -0.4781 0.07571 0.06900 -0.0432 1.0000 0.0630
-7.250 -0.4927 0.07139 0.06466 -0.0432 1.0000 0.0630
-7.000 -0.5030 0.06726 0.06047 -0.0430 1.0000 0.0632
-6.750 -0.5091 0.06333 0.05642 -0.0427 1.0000 0.0639
-6.500 -0.4959 0.05790 0.05067 -0.0466 0.9948 0.0655
-6.250 -0.4758 0.05174 0.04397 -0.0514 0.9874 0.0676
-6.000 -0.4529 0.04536 0.03675 -0.0554 0.9810 0.0702
-5.750 -0.4258 0.04216 0.03315 -0.0576 0.9745 0.0728
-5.500 -0.3956 0.04008 0.03077 -0.0595 0.9688 0.0769
-5.250 -0.3668 0.03734 0.02741 -0.0612 0.9623 0.0842
-5.000 -0.3326 0.03625 0.02600 -0.0634 0.9571 0.0946
-4.750 -0.3063 0.03579 0.02552 -0.0641 0.9492 0.1056
-4.500 -0.2728 0.03482 0.02432 -0.0660 0.9440 0.1185
-4.250 -0.2438 0.03337 0.02230 -0.0667 0.9371 0.1274
-4.000 -0.2123 0.03250 0.02144 -0.0680 0.9312 0.1359
-3.750 -0.1759 0.03134 0.01987 -0.0698 0.9268 0.1439
-3.500 -0.1504 0.03071 0.01924 -0.0698 0.9191 0.1515
-3.250 -0.1153 0.03003 0.01839 -0.0714 0.9141 0.1625
-3.000 -0.0853 0.02949 0.01768 -0.0720 0.9078 0.1725
-2.750 -0.0545 0.02901 0.01718 -0.0728 0.9015 0.1831
-2.500 -0.0172 0.02858 0.01667 -0.0747 0.8972 0.1994
-2.250 0.0072 0.02836 0.01642 -0.0744 0.8894 0.2153
-2.000 0.0413 0.02802 0.01609 -0.0758 0.8841 0.2383
-1.750 0.0712 0.02769 0.01584 -0.0765 0.8780 0.2632
-1.500 0.0994 0.02735 0.01562 -0.0769 0.8713 0.2935
-1.250 0.1347 0.02670 0.01532 -0.0785 0.8670 0.3568
-1.000 0.1539 0.02611 0.01539 -0.0773 0.8589 0.4759
-0.750 0.2117 0.02494 0.01546 -0.0812 0.8560 1.0000
-0.500 0.2483 0.02502 0.01521 -0.0828 0.8512 1.0000
-0.250 0.2663 0.02539 0.01538 -0.0814 0.8412 1.0000
0.000 0.3026 0.02545 0.01520 -0.0829 0.8362 1.0000
0.250 0.3212 0.02583 0.01542 -0.0815 0.8260 1.0000
0.500 0.3533 0.02587 0.01529 -0.0821 0.8182 1.0000
0.750 0.3830 0.02587 0.01515 -0.0821 0.8082 1.0000
1.000 0.4088 0.02594 0.01509 -0.0815 0.7968 1.0000
1.250 0.4432 0.02577 0.01480 -0.0821 0.7883 1.0000
1.500 0.4698 0.02585 0.01479 -0.0816 0.7779 1.0000
1.750 0.4942 0.02604 0.01492 -0.0808 0.7679 1.0000
2.000 0.5275 0.02596 0.01476 -0.0813 0.7607 1.0000
2.250 0.5487 0.02629 0.01506 -0.0802 0.7498 1.0000
2.500 0.5827 0.02618 0.01489 -0.0807 0.7431 1.0000
2.750 0.6044 0.02649 0.01519 -0.0796 0.7318 1.0000
3.000 0.6288 0.02671 0.01542 -0.0788 0.7214 1.0000
3.250 0.6617 0.02660 0.01529 -0.0791 0.7135 1.0000
3.500 0.6825 0.02696 0.01567 -0.0778 0.7014 1.0000
3.750 0.7075 0.02715 0.01589 -0.0771 0.6904 1.0000
4.000 0.7401 0.02702 0.01577 -0.0772 0.6817 1.0000
4.500 0.7833 0.02766 0.01652 -0.0748 0.6559 1.0000
4.750 0.8082 0.02784 0.01675 -0.0740 0.6438 1.0000
5.000 0.8374 0.02782 0.01677 -0.0736 0.6328 1.0000
5.250 0.8623 0.02796 0.01698 -0.0727 0.6196 1.0000
5.500 0.8847 0.02816 0.01725 -0.0714 0.6048 1.0000
5.750 0.9078 0.02828 0.01742 -0.0702 0.5894 1.0000
6.000 0.9315 0.02831 0.01749 -0.0689 0.5732 1.0000
6.250 0.9515 0.02849 0.01773 -0.0672 0.5550 1.0000
6.500 0.9706 0.02873 0.01802 -0.0654 0.5364 1.0000
6.750 0.9914 0.02895 0.01829 -0.0639 0.5189 1.0000
7.000 1.0127 0.02924 0.01861 -0.0625 0.5025 1.0000
7.250 1.0341 0.02958 0.01903 -0.0613 0.4867 1.0000
7.500 1.0551 0.02995 0.01945 -0.0599 0.4708 1.0000
7.750 1.0756 0.03037 0.01990 -0.0585 0.4546 1.0000
8.000 1.0955 0.03084 0.02041 -0.0571 0.4383 1.0000
8.250 1.1148 0.03136 0.02097 -0.0556 0.4216 1.0000
8.500 1.1331 0.03191 0.02150 -0.0539 0.4041 1.0000
8.750 1.1464 0.03270 0.02235 -0.0518 0.3856 1.0000
9.000 1.1583 0.03353 0.02320 -0.0495 0.3665 1.0000
9.250 1.1686 0.03441 0.02410 -0.0470 0.3479 1.0000
9.500 1.1783 0.03538 0.02507 -0.0445 0.3297 1.0000
9.750 1.1873 0.03644 0.02614 -0.0421 0.3122 1.0000
10.000 1.1952 0.03762 0.02735 -0.0398 0.2954 1.0000
10.250 1.2014 0.03893 0.02872 -0.0374 0.2792 1.0000
10.500 1.2064 0.04037 0.03025 -0.0352 0.2635 1.0000
10.750 1.2117 0.04187 0.03184 -0.0331 0.2489 1.0000
11.000 1.2167 0.04344 0.03346 -0.0312 0.2352 1.0000
11.250 1.2212 0.04513 0.03523 -0.0294 0.2223 1.0000
11.500 1.2259 0.04694 0.03712 -0.0277 0.2102 1.0000
11.750 1.2304 0.04883 0.03908 -0.0262 0.1989 1.0000
12.000 1.2351 0.05076 0.04102 -0.0247 0.1884 1.0000
12.250 1.2417 0.05256 0.04274 -0.0233 0.1785 1.0000
12.500 1.2450 0.05488 0.04526 -0.0221 0.1686 1.0000
12.750 1.2480 0.05721 0.04765 -0.0209 0.1591 1.0000
13.000 1.2514 0.05935 0.04973 -0.0197 0.1495 1.0000
13.250 1.2443 0.06276 0.05342 -0.0190 0.1410 1.0000
13.500 1.2416 0.06556 0.05622 -0.0183 0.1328 1.0000
13.750 1.2330 0.06929 0.06019 -0.0181 0.1253 1.0000
14.000 1.2286 0.07252 0.06348 -0.0179 0.1185 1.0000
14.250 1.2198 0.07663 0.06783 -0.0182 0.1122 1.0000
14.500 1.2174 0.07977 0.07096 -0.0181 0.1065 1.0000
14.750 1.2060 0.08472 0.07623 -0.0190 0.1012 1.0000
15.000 1.2023 0.08829 0.07984 -0.0194 0.0961 1.0000
15.250 1.1930 0.09315 0.08489 -0.0205 0.0918 1.0000
15.500 1.1796 0.09893 0.09091 -0.0223 0.0879 1.0000
15.750 1.1802 0.10188 0.09379 -0.0228 0.0830 1.0000
16.000 1.1636 0.10868 0.10083 -0.0255 0.0801 1.0000
16.250 1.1405 0.11728 0.10972 -0.0296 0.0781 1.0000
16.500 1.1114 0.12785 0.12051 -0.0351 0.0770 1.0000
16.750 1.0593 0.14566 0.13850 -0.0454 0.0776 1.0000
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