Rhode St. Genese 34 (rhodesg34-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Rhode St. Genese 34 (rhodesg34-il) Reynolds number: 100,000 Max Cl/Cd: 43.8 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg34-il-100000.txt Download as CSV file: xf-rhodesg34-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: Rhode St. Genese 34
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3213 0.11368 0.10918 -0.0221 1.0000 0.1179
-10.500 -0.3354 0.11247 0.10804 -0.0211 1.0000 0.1208
-10.250 -0.3748 0.11232 0.10799 -0.0249 0.9978 0.1232
-10.000 -0.3451 0.10660 0.10226 -0.0277 0.9937 0.1252
-9.750 -0.3070 0.10263 0.09825 -0.0293 0.9885 0.1295
-9.500 -0.3057 0.09969 0.09532 -0.0371 0.9805 0.1361
-9.250 -0.3234 0.09560 0.09126 -0.0468 0.9693 0.1385
-9.000 -0.2660 0.09141 0.08703 -0.0443 0.9662 0.1426
-8.750 -0.2546 0.08829 0.08392 -0.0481 0.9573 0.1478
-8.500 -0.2795 0.08369 0.07923 -0.0602 0.9422 0.1537
-8.250 -0.2323 0.07989 0.07547 -0.0593 0.9397 0.1570
-8.000 -0.2213 0.07736 0.07294 -0.0596 0.9292 0.1616
-7.750 -0.2276 0.07294 0.06835 -0.0678 0.9168 0.1706
-7.500 -0.1949 0.06975 0.06522 -0.0677 0.9107 0.1741
-7.250 -0.1945 0.06684 0.06200 -0.0733 0.8988 0.1870
-7.000 -0.1597 0.06318 0.05850 -0.0730 0.8933 0.1909
-6.750 -0.1341 0.05958 0.05464 -0.0786 0.8860 0.2060
-6.500 -0.1143 0.05696 0.05209 -0.0774 0.8761 0.2095
-6.250 -0.0852 0.04383 0.03715 -0.0873 0.8707 0.1231
-6.000 -0.0755 0.04181 0.03519 -0.0847 0.8584 0.1203
-5.750 -0.0386 0.03673 0.02903 -0.0867 0.8543 0.1106
-5.500 -0.0202 0.03507 0.02713 -0.0850 0.8445 0.1103
-5.250 0.0196 0.03265 0.02438 -0.0867 0.8388 0.1098
-5.000 0.0682 0.03026 0.02157 -0.0895 0.8351 0.1103
-4.750 0.0852 0.02936 0.02056 -0.0873 0.8239 0.1124
-4.500 0.1297 0.02799 0.01915 -0.0894 0.8187 0.1171
-4.250 0.1576 0.02705 0.01805 -0.0886 0.8094 0.1206
-4.000 0.1955 0.02573 0.01661 -0.0894 0.8018 0.1255
-3.750 0.2281 0.02492 0.01581 -0.0893 0.7928 0.1337
-3.500 0.2622 0.02382 0.01472 -0.0894 0.7833 0.1424
-3.250 0.2886 0.02306 0.01395 -0.0882 0.7714 0.1547
-3.000 0.3268 0.02169 0.01272 -0.0889 0.7628 0.1764
-2.750 0.3469 0.02070 0.01198 -0.0867 0.7483 0.2116
-2.500 0.3689 0.01929 0.01117 -0.0848 0.7341 0.3198
-2.250 0.5227 0.01627 0.00984 -0.1058 0.7127 1.0000
-2.000 0.5427 0.01589 0.00923 -0.1035 0.6890 1.0000
-1.750 0.5649 0.01555 0.00858 -0.1016 0.6607 1.0000
-1.500 0.5865 0.01543 0.00810 -0.0997 0.6277 1.0000
-1.250 0.6069 0.01559 0.00788 -0.0979 0.5953 1.0000
-1.000 0.6279 0.01586 0.00777 -0.0963 0.5693 1.0000
-0.750 0.6472 0.01619 0.00785 -0.0946 0.5475 1.0000
-0.500 0.6684 0.01651 0.00792 -0.0932 0.5316 1.0000
-0.250 0.6904 0.01684 0.00803 -0.0921 0.5189 1.0000
0.000 0.7121 0.01720 0.00824 -0.0910 0.5080 1.0000
0.250 0.7369 0.01757 0.00836 -0.0904 0.4999 1.0000
0.500 0.7587 0.01796 0.00868 -0.0894 0.4919 1.0000
0.750 0.7835 0.01834 0.00890 -0.0889 0.4855 1.0000
1.000 0.8077 0.01879 0.00924 -0.0883 0.4801 1.0000
1.250 0.8307 0.01923 0.00964 -0.0876 0.4746 1.0000
1.500 0.8557 0.01967 0.00996 -0.0871 0.4698 1.0000
1.750 0.8832 0.02017 0.01030 -0.0872 0.4657 1.0000
2.000 0.9038 0.02068 0.01087 -0.0861 0.4615 1.0000
2.250 0.9266 0.02120 0.01139 -0.0854 0.4577 1.0000
2.500 0.9509 0.02174 0.01191 -0.0850 0.4544 1.0000
2.750 0.9766 0.02230 0.01241 -0.0849 0.4516 1.0000
3.000 1.0043 0.02293 0.01295 -0.0851 0.4491 1.0000
3.250 1.0247 0.02359 0.01370 -0.0841 0.4463 1.0000
3.500 1.0439 0.02425 0.01446 -0.0829 0.4431 1.0000
3.750 1.0647 0.02491 0.01518 -0.0821 0.4398 1.0000
4.000 1.0874 0.02553 0.01583 -0.0815 0.4365 1.0000
4.250 1.1134 0.02616 0.01640 -0.0815 0.4332 1.0000
4.500 1.1372 0.02692 0.01715 -0.0811 0.4299 1.0000
4.750 1.1513 0.02771 0.01813 -0.0793 0.4264 1.0000
5.000 1.1690 0.02851 0.01904 -0.0780 0.4231 1.0000
5.250 1.1888 0.02931 0.01992 -0.0772 0.4202 1.0000
5.500 1.2116 0.03006 0.02070 -0.0767 0.4173 1.0000
5.750 1.2417 0.03077 0.02133 -0.0775 0.4137 1.0000
6.000 1.2504 0.03185 0.02263 -0.0750 0.4107 1.0000
6.250 1.2595 0.03290 0.02387 -0.0726 0.4068 1.0000
6.500 1.2791 0.03353 0.02455 -0.0717 0.4018 1.0000
6.750 1.3148 0.03381 0.02469 -0.0731 0.3964 1.0000
7.000 1.3193 0.03501 0.02610 -0.0701 0.3924 1.0000
7.250 1.3246 0.03607 0.02734 -0.0673 0.3875 1.0000
7.500 1.3512 0.03635 0.02761 -0.0673 0.3818 1.0000
7.750 1.3839 0.03685 0.02803 -0.0684 0.3769 1.0000
8.000 1.3751 0.03836 0.02984 -0.0637 0.3729 1.0000
8.250 1.3799 0.03945 0.03109 -0.0610 0.3682 1.0000
8.500 1.4126 0.03954 0.03116 -0.0618 0.3628 1.0000
8.750 1.4349 0.04026 0.03191 -0.0615 0.3581 1.0000
9.000 1.4146 0.04219 0.03412 -0.0556 0.3540 1.0000
9.250 1.4207 0.04305 0.03509 -0.0531 0.3487 1.0000
9.500 1.4872 0.04185 0.03370 -0.0582 0.3414 1.0000
9.750 1.4479 0.04415 0.03632 -0.0498 0.3377 1.0000
10.000 1.4220 0.04621 0.03856 -0.0438 0.3332 1.0000
10.250 1.5229 0.04330 0.03541 -0.0526 0.3240 1.0000
10.500 1.4682 0.04615 0.03857 -0.0428 0.3208 1.0000
10.750 1.4171 0.04995 0.04260 -0.0358 0.3164 1.0000
11.000 1.4921 0.04680 0.03936 -0.0395 0.3088 1.0000
11.250 1.4705 0.04909 0.04181 -0.0353 0.3039 1.0000
11.500 1.0447 0.09995 0.09293 -0.0336 0.2723 1.0000
11.750 1.1013 0.09363 0.08672 -0.0309 0.2731 1.0000
12.000 1.1565 0.08740 0.08059 -0.0283 0.2732 1.0000
12.250 1.2219 0.08026 0.07355 -0.0259 0.2729 1.0000
12.500 1.3186 0.06998 0.06336 -0.0237 0.2720 1.0000
13.000 1.3112 0.07487 0.06841 -0.0232 0.2577 1.0000
13.750 0.9738 0.14399 0.13738 -0.0465 0.2100 1.0000
14.000 0.9994 0.14228 0.13576 -0.0454 0.2047 1.0000
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Polar data table (+)
Polar graphs
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