Rhode St. Genese 36 (rhodesg36-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 36 (rhodesg36-il) Reynolds number: 100,000 Max Cl/Cd: 41.84 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg36-il-100000-n5.txt Download as CSV file: xf-rhodesg36-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.1479 0.12895 0.12363 -0.0590 0.9798 0.0788
-13.750 -0.1456 0.12534 0.12002 -0.0642 0.9750 0.0801
-13.500 -0.1383 0.12128 0.11596 -0.0695 0.9716 0.0805
-13.250 -0.1072 0.11773 0.11240 -0.0703 0.9699 0.0819
-13.000 -0.0908 0.11484 0.10951 -0.0722 0.9650 0.0844
-12.750 -0.0876 0.11110 0.10577 -0.0784 0.9609 0.0880
-11.750 -0.0519 0.09196 0.08653 -0.0935 0.9401 0.0656
-11.500 -0.0329 0.08859 0.08315 -0.0964 0.9360 0.0645
-11.250 -0.0304 0.08517 0.07975 -0.0981 0.9257 0.0643
-11.000 -0.0307 0.08182 0.07642 -0.0995 0.9144 0.0642
-10.750 -0.0334 0.07839 0.07300 -0.1007 0.9017 0.0639
-10.500 -0.0389 0.07473 0.06936 -0.1020 0.8890 0.0634
-10.000 -0.1368 0.05600 0.05023 -0.1122 0.8591 0.0596
-9.750 -0.1493 0.05134 0.04530 -0.1119 0.8493 0.0594
-9.500 -0.1574 0.04641 0.03993 -0.1115 0.8412 0.0595
-9.250 -0.1641 0.04238 0.03539 -0.1096 0.8316 0.0598
-9.000 -0.1387 0.04111 0.03412 -0.1096 0.8249 0.0606
-8.750 -0.1206 0.03922 0.03205 -0.1089 0.8173 0.0615
-8.500 -0.1069 0.03714 0.02968 -0.1076 0.8084 0.0626
-8.250 -0.0865 0.03459 0.02668 -0.1073 0.8032 0.0636
-8.000 -0.0756 0.03292 0.02466 -0.1051 0.7934 0.0642
-7.750 -0.0540 0.03102 0.02232 -0.1043 0.7870 0.0651
-7.500 -0.0331 0.02952 0.02035 -0.1032 0.7803 0.0661
-7.250 -0.0126 0.02861 0.01943 -0.1020 0.7717 0.0672
-7.000 0.0160 0.02760 0.01832 -0.1020 0.7660 0.0689
-6.750 0.0349 0.02684 0.01740 -0.1004 0.7566 0.0705
-6.500 0.0607 0.02586 0.01614 -0.0997 0.7489 0.0720
-6.250 0.0849 0.02505 0.01511 -0.0987 0.7412 0.0732
-6.000 0.1078 0.02430 0.01438 -0.0977 0.7319 0.0746
-5.750 0.1336 0.02361 0.01363 -0.0970 0.7232 0.0769
-5.500 0.1562 0.02305 0.01296 -0.0958 0.7130 0.0791
-5.250 0.1818 0.02241 0.01225 -0.0951 0.7045 0.0812
-5.000 0.2044 0.02188 0.01176 -0.0939 0.6947 0.0830
-4.750 0.2298 0.02137 0.01121 -0.0932 0.6858 0.0858
-4.500 0.2531 0.02095 0.01074 -0.0921 0.6757 0.0888
-4.250 0.2772 0.02052 0.01034 -0.0912 0.6657 0.0920
-4.000 0.3019 0.02015 0.00991 -0.0902 0.6546 0.0954
-3.750 0.3242 0.01987 0.00966 -0.0890 0.6422 0.0996
-3.500 0.3496 0.01959 0.00932 -0.0882 0.6297 0.1057
-3.250 0.3721 0.01941 0.00917 -0.0869 0.6152 0.1129
-3.000 0.3934 0.01929 0.00904 -0.0855 0.5992 0.1234
-2.750 0.4147 0.01919 0.00891 -0.0840 0.5821 0.1409
-2.500 0.4347 0.01910 0.00877 -0.0824 0.5626 0.1622
-2.250 0.4536 0.01900 0.00865 -0.0806 0.5394 0.1834
-2.000 0.4723 0.01891 0.00854 -0.0789 0.5123 0.2082
-1.750 0.4910 0.01888 0.00844 -0.0771 0.4849 0.2398
-1.500 0.5095 0.01889 0.00839 -0.0755 0.4633 0.2870
-1.250 0.5276 0.01874 0.00846 -0.0740 0.4471 0.3965
-1.000 0.5426 0.01804 0.00876 -0.0712 0.4352 0.7188
-0.750 0.6538 0.01856 0.00926 -0.0873 0.4173 1.0000
-0.500 0.6710 0.01887 0.00937 -0.0855 0.4103 1.0000
-0.250 0.6895 0.01921 0.00948 -0.0839 0.4046 1.0000
0.000 0.7087 0.01949 0.00966 -0.0824 0.3992 1.0000
0.250 0.7284 0.01980 0.00983 -0.0810 0.3940 1.0000
0.500 0.7491 0.02014 0.01001 -0.0798 0.3894 1.0000
1.000 0.7929 0.02083 0.01042 -0.0780 0.3810 1.0000
1.250 0.8139 0.02116 0.01068 -0.0769 0.3768 1.0000
1.500 0.8357 0.02151 0.01093 -0.0760 0.3729 1.0000
1.750 0.8589 0.02188 0.01119 -0.0754 0.3695 1.0000
2.000 0.8847 0.02228 0.01145 -0.0753 0.3666 1.0000
2.250 0.9098 0.02269 0.01176 -0.0750 0.3638 1.0000
2.500 0.9314 0.02307 0.01214 -0.0742 0.3611 1.0000
2.750 0.9537 0.02347 0.01252 -0.0735 0.3583 1.0000
3.000 0.9764 0.02389 0.01291 -0.0730 0.3557 1.0000
3.250 0.9997 0.02433 0.01331 -0.0725 0.3531 1.0000
3.500 1.0233 0.02477 0.01370 -0.0721 0.3506 1.0000
3.750 1.0482 0.02523 0.01409 -0.0720 0.3482 1.0000
4.000 1.0756 0.02574 0.01451 -0.0723 0.3459 1.0000
4.250 1.0987 0.02626 0.01502 -0.0719 0.3438 1.0000
4.500 1.1176 0.02677 0.01559 -0.0709 0.3416 1.0000
4.750 1.1375 0.02730 0.01619 -0.0700 0.3396 1.0000
5.000 1.1573 0.02786 0.01679 -0.0691 0.3376 1.0000
5.250 1.1773 0.02843 0.01739 -0.0683 0.3357 1.0000
5.500 1.1977 0.02902 0.01801 -0.0676 0.3339 1.0000
5.750 1.2186 0.02962 0.01863 -0.0671 0.3321 1.0000
6.000 1.2401 0.03022 0.01925 -0.0666 0.3304 1.0000
6.250 1.2629 0.03083 0.01986 -0.0664 0.3287 1.0000
6.500 1.2882 0.03146 0.02048 -0.0666 0.3271 1.0000
6.750 1.3169 0.03217 0.02115 -0.0674 0.3254 1.0000
7.000 1.3239 0.03294 0.02208 -0.0648 0.3238 1.0000
7.250 1.3324 0.03380 0.02308 -0.0625 0.3223 1.0000
7.500 1.3413 0.03471 0.02413 -0.0604 0.3207 1.0000
7.750 1.3502 0.03569 0.02523 -0.0584 0.3191 1.0000
8.000 1.3588 0.03672 0.02639 -0.0565 0.3176 1.0000
8.250 1.3673 0.03779 0.02757 -0.0546 0.3160 1.0000
8.500 1.3760 0.03886 0.02875 -0.0529 0.3143 1.0000
8.750 1.3874 0.03981 0.02978 -0.0515 0.3123 1.0000
9.000 1.4055 0.04047 0.03046 -0.0510 0.3101 1.0000
9.250 1.4332 0.04087 0.03082 -0.0515 0.3078 1.0000
9.500 1.4505 0.04174 0.03173 -0.0510 0.3057 1.0000
9.750 1.4295 0.04392 0.03418 -0.0464 0.3037 1.0000
10.000 1.4061 0.04660 0.03710 -0.0422 0.3014 1.0000
10.250 1.3814 0.04981 0.04054 -0.0387 0.2990 1.0000
10.500 1.3539 0.05367 0.04461 -0.0358 0.2966 1.0000
10.750 1.3381 0.05696 0.04803 -0.0340 0.2939 1.0000
11.000 1.3676 0.05652 0.04757 -0.0342 0.2913 1.0000
11.250 1.4267 0.05402 0.04494 -0.0360 0.2890 1.0000
11.750 0.9853 0.11651 0.10840 -0.0406 0.2565 1.0000
12.000 0.9585 0.12443 0.11640 -0.0430 0.2486 1.0000
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Polar data table (+)
Polar graphs
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