Rhode St. Genese 36 (rhodesg36-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 36 (rhodesg36-il) Reynolds number: 50,000 Max Cl/Cd: 27.78 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg36-il-50000-n5.txt Download as CSV file: xf-rhodesg36-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Rhode St. Genese 36
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1576 0.10422 0.09728 -0.0683 0.9382 0.1058
-10.500 -0.1380 0.10135 0.09442 -0.0685 0.9322 0.1028
-10.250 -0.1540 0.09619 0.08924 -0.0737 0.9225 0.0965
-10.000 -0.1509 0.09348 0.08656 -0.0744 0.9141 0.0959
-9.750 -0.1566 0.09099 0.08410 -0.0745 0.9046 0.0952
-9.500 -0.1640 0.08804 0.08117 -0.0756 0.8957 0.0947
-9.250 -0.1679 0.08448 0.07760 -0.0775 0.8871 0.0940
-9.000 -0.1788 0.08133 0.07442 -0.0776 0.8768 0.0933
-8.750 -0.1785 0.07673 0.06972 -0.0807 0.8702 0.0920
-8.500 -0.1941 0.07306 0.06594 -0.0802 0.8601 0.0908
-8.250 -0.2076 0.06678 0.05926 -0.0823 0.8521 0.0888
-8.000 -0.2071 0.06290 0.05507 -0.0822 0.8434 0.0882
-7.750 -0.1940 0.05888 0.05067 -0.0833 0.8367 0.0884
-7.500 -0.1809 0.05722 0.04897 -0.0821 0.8267 0.0894
-7.250 -0.1475 0.05437 0.04589 -0.0844 0.8208 0.0913
-7.000 -0.1400 0.05224 0.04351 -0.0823 0.8084 0.0923
-6.750 -0.1036 0.04848 0.03924 -0.0848 0.8026 0.0935
-6.500 -0.0950 0.04656 0.03700 -0.0822 0.7893 0.0941
-6.250 -0.0576 0.04338 0.03321 -0.0839 0.7841 0.0964
-6.000 -0.0484 0.04255 0.03227 -0.0811 0.7715 0.0980
-5.750 -0.0115 0.04099 0.03056 -0.0822 0.7663 0.1008
-5.500 0.0005 0.04013 0.02951 -0.0798 0.7553 0.1024
-5.250 0.0343 0.03838 0.02737 -0.0802 0.7489 0.1051
-5.000 0.0552 0.03766 0.02659 -0.0789 0.7391 0.1079
-4.750 0.0850 0.03669 0.02551 -0.0787 0.7308 0.1119
-4.500 0.1121 0.03568 0.02423 -0.0779 0.7219 0.1155
-4.250 0.1396 0.03491 0.02349 -0.0773 0.7122 0.1192
-4.000 0.1646 0.03425 0.02268 -0.0763 0.7017 0.1248
-3.750 0.1989 0.03331 0.02170 -0.0765 0.6926 0.1310
-3.500 0.2226 0.03276 0.02100 -0.0752 0.6804 0.1376
-3.250 0.2648 0.03167 0.01982 -0.0765 0.6723 0.1497
-3.000 0.2843 0.03121 0.01938 -0.0747 0.6581 0.1592
-2.750 0.3156 0.03034 0.01849 -0.0745 0.6465 0.1775
-2.500 0.3474 0.02936 0.01760 -0.0745 0.6345 0.2057
-2.250 0.3679 0.02884 0.01722 -0.0729 0.6190 0.2415
-2.000 0.3936 0.02811 0.01673 -0.0722 0.6046 0.3012
-1.500 0.5150 0.02575 0.01605 -0.0819 0.5689 1.0000
-1.250 0.5356 0.02581 0.01578 -0.0803 0.5525 1.0000
-1.000 0.5509 0.02607 0.01579 -0.0781 0.5355 1.0000
-0.750 0.5677 0.02634 0.01581 -0.0761 0.5201 1.0000
-0.500 0.5873 0.02659 0.01579 -0.0746 0.5070 1.0000
-0.250 0.6117 0.02673 0.01562 -0.0738 0.4965 1.0000
0.000 0.6302 0.02711 0.01579 -0.0723 0.4857 1.0000
0.250 0.6542 0.02737 0.01576 -0.0715 0.4770 1.0000
0.500 0.6743 0.02779 0.01598 -0.0703 0.4682 1.0000
0.750 0.7019 0.02804 0.01594 -0.0702 0.4612 1.0000
1.000 0.7195 0.02862 0.01641 -0.0688 0.4535 1.0000
1.250 0.7451 0.02903 0.01661 -0.0685 0.4472 1.0000
1.500 0.7730 0.02945 0.01682 -0.0686 0.4419 1.0000
1.750 0.7914 0.03014 0.01746 -0.0675 0.4364 1.0000
2.000 0.8152 0.03071 0.01793 -0.0671 0.4314 1.0000
2.250 0.8452 0.03117 0.01822 -0.0676 0.4270 1.0000
2.500 0.8717 0.03175 0.01868 -0.0677 0.4228 1.0000
2.750 0.8857 0.03263 0.01959 -0.0661 0.4182 1.0000
3.000 0.9047 0.03340 0.02034 -0.0652 0.4138 1.0000
3.250 0.9300 0.03405 0.02090 -0.0651 0.4099 1.0000
3.500 0.9615 0.03461 0.02133 -0.0660 0.4067 1.0000
3.750 0.9844 0.03544 0.02212 -0.0657 0.4038 1.0000
4.000 0.9900 0.03669 0.02349 -0.0632 0.4006 1.0000
4.250 0.9974 0.03795 0.02482 -0.0610 0.3975 1.0000
4.500 1.0080 0.03916 0.02608 -0.0592 0.3943 1.0000
4.750 1.0237 0.04023 0.02717 -0.0582 0.3914 1.0000
5.000 1.0467 0.04110 0.02800 -0.0580 0.3886 1.0000
5.250 1.0788 0.04174 0.02857 -0.0591 0.3862 1.0000
5.500 1.0797 0.04342 0.03035 -0.0564 0.3836 1.0000
5.750 1.0451 0.04679 0.03397 -0.0505 0.3802 1.0000
6.000 0.9955 0.05205 0.03948 -0.0450 0.3760 1.0000
6.250 0.9455 0.05879 0.04642 -0.0416 0.3712 1.0000
6.500 0.9449 0.06181 0.04948 -0.0408 0.3683 1.0000
6.750 0.9654 0.06285 0.05051 -0.0405 0.3664 1.0000
7.250 0.7867 0.09220 0.08033 -0.0423 0.3485 1.0000
7.500 0.8032 0.09378 0.08191 -0.0422 0.3467 1.0000
7.750 0.8243 0.09481 0.08293 -0.0419 0.3453 1.0000
8.000 0.7657 0.10610 0.09436 -0.0442 0.3391 1.0000
8.250 0.7592 0.11062 0.09893 -0.0450 0.3362 1.0000
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Polar data table (+)
Polar graphs
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