Rhode St. Genese 32 (rhodesg32-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 32 (rhodesg32-il) Reynolds number: 50,000 Max Cl/Cd: 33.4 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg32-il-50000-n5.txt Download as CSV file: xf-rhodesg32-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Rhode St. Genese 32
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3214 0.10073 0.09382 -0.0332 1.0000 0.1583
-10.000 -0.3746 0.09450 0.08774 -0.0377 1.0000 0.1068
-9.750 -0.3782 0.09224 0.08555 -0.0354 1.0000 0.1058
-9.500 -0.3889 0.09015 0.08355 -0.0331 1.0000 0.1045
-9.000 -0.4477 0.08135 0.07481 -0.0365 1.0000 0.0950
-8.750 -0.4490 0.07896 0.07246 -0.0346 1.0000 0.0943
-8.500 -0.4521 0.07629 0.06980 -0.0332 1.0000 0.0935
-8.250 -0.4492 0.07271 0.06617 -0.0342 0.9978 0.0924
-8.000 -0.4308 0.06752 0.06078 -0.0395 0.9899 0.0919
-7.750 -0.4113 0.06232 0.05527 -0.0447 0.9821 0.0926
-7.500 -0.3911 0.05768 0.05030 -0.0486 0.9742 0.0928
-7.250 -0.3692 0.05360 0.04588 -0.0514 0.9666 0.0924
-7.000 -0.3432 0.04972 0.04158 -0.0545 0.9596 0.0922
-6.750 -0.3200 0.04634 0.03772 -0.0562 0.9511 0.0933
-6.500 -0.2879 0.04292 0.03360 -0.0591 0.9442 0.0949
-6.250 -0.2619 0.04076 0.03118 -0.0599 0.9343 0.0958
-6.000 -0.2266 0.03865 0.02874 -0.0620 0.9263 0.0966
-5.750 -0.1945 0.03693 0.02675 -0.0632 0.9162 0.0978
-5.500 -0.1609 0.03555 0.02515 -0.0645 0.9061 0.1007
-5.250 -0.1206 0.03394 0.02317 -0.0668 0.8974 0.1038
-5.000 -0.0900 0.03259 0.02148 -0.0671 0.8864 0.1056
-4.750 -0.0474 0.03114 0.01972 -0.0693 0.8785 0.1077
-4.500 -0.0146 0.03023 0.01879 -0.0700 0.8670 0.1108
-4.250 0.0189 0.02938 0.01783 -0.0705 0.8548 0.1157
-4.000 0.0570 0.02838 0.01661 -0.0714 0.8436 0.1204
-3.750 0.0938 0.02749 0.01572 -0.0724 0.8327 0.1247
-3.500 0.1226 0.02689 0.01502 -0.0720 0.8201 0.1303
-3.250 0.1525 0.02631 0.01442 -0.0718 0.8088 0.1391
-3.000 0.1873 0.02557 0.01364 -0.0724 0.7990 0.1517
-2.750 0.2124 0.02498 0.01307 -0.0714 0.7852 0.1664
-2.500 0.2383 0.02427 0.01250 -0.0707 0.7713 0.1951
-2.250 0.2640 0.02328 0.01201 -0.0701 0.7570 0.2735
-2.000 0.3492 0.02068 0.01152 -0.0789 0.7428 1.0000
-1.750 0.3737 0.02059 0.01114 -0.0777 0.7249 1.0000
-1.500 0.3989 0.02050 0.01079 -0.0766 0.7059 1.0000
-1.250 0.4252 0.02040 0.01044 -0.0757 0.6860 1.0000
-1.000 0.4499 0.02037 0.01018 -0.0745 0.6634 1.0000
-0.750 0.4747 0.02038 0.00994 -0.0734 0.6394 1.0000
-0.500 0.4999 0.02043 0.00973 -0.0723 0.6149 1.0000
-0.250 0.5234 0.02059 0.00964 -0.0712 0.5896 1.0000
0.000 0.5476 0.02079 0.00956 -0.0701 0.5669 1.0000
0.250 0.5703 0.02108 0.00964 -0.0690 0.5458 1.0000
0.500 0.5938 0.02140 0.00974 -0.0681 0.5286 1.0000
0.750 0.6177 0.02175 0.00988 -0.0673 0.5149 1.0000
1.000 0.6420 0.02212 0.01007 -0.0666 0.5035 1.0000
1.250 0.6659 0.02254 0.01037 -0.0660 0.4935 1.0000
1.500 0.6916 0.02293 0.01059 -0.0656 0.4861 1.0000
1.750 0.7158 0.02340 0.01102 -0.0652 0.4783 1.0000
2.000 0.7418 0.02383 0.01134 -0.0649 0.4721 1.0000
2.250 0.7669 0.02432 0.01178 -0.0646 0.4663 1.0000
2.500 0.7920 0.02482 0.01227 -0.0643 0.4608 1.0000
2.750 0.8186 0.02530 0.01270 -0.0642 0.4563 1.0000
3.000 0.8445 0.02584 0.01322 -0.0641 0.4523 1.0000
3.250 0.8685 0.02646 0.01392 -0.0638 0.4484 1.0000
3.500 0.8933 0.02708 0.01458 -0.0635 0.4449 1.0000
3.750 0.9189 0.02769 0.01523 -0.0634 0.4419 1.0000
4.000 0.9455 0.02831 0.01588 -0.0635 0.4394 1.0000
4.250 0.9696 0.02904 0.01669 -0.0632 0.4368 1.0000
4.500 0.9899 0.02989 0.01770 -0.0625 0.4333 1.0000
4.750 1.0110 0.03066 0.01859 -0.0618 0.4290 1.0000
5.000 1.0359 0.03128 0.01923 -0.0616 0.4244 1.0000
5.250 1.0572 0.03203 0.02007 -0.0609 0.4197 1.0000
5.500 1.0734 0.03295 0.02117 -0.0596 0.4140 1.0000
5.750 1.0972 0.03356 0.02184 -0.0591 0.4086 1.0000
6.000 1.1184 0.03434 0.02271 -0.0584 0.4037 1.0000
6.250 1.1310 0.03546 0.02405 -0.0568 0.3985 1.0000
6.500 1.1519 0.03622 0.02494 -0.0561 0.3932 1.0000
6.750 1.1763 0.03687 0.02564 -0.0557 0.3880 1.0000
7.000 1.1823 0.03824 0.02728 -0.0534 0.3821 1.0000
7.250 1.2020 0.03902 0.02819 -0.0525 0.3762 1.0000
7.500 1.2241 0.03974 0.02903 -0.0519 0.3706 1.0000
7.750 1.2246 0.04133 0.03089 -0.0490 0.3642 1.0000
8.000 1.2525 0.04157 0.03118 -0.0489 0.3566 1.0000
8.250 1.2504 0.04310 0.03295 -0.0456 0.3490 1.0000
8.500 1.2831 0.04266 0.03248 -0.0457 0.3379 1.0000
8.750 1.2646 0.04477 0.03491 -0.0408 0.3302 1.0000
9.000 1.2873 0.04462 0.03479 -0.0398 0.3196 1.0000
9.250 1.2642 0.04695 0.03737 -0.0347 0.3126 1.0000
9.500 1.2853 0.04684 0.03731 -0.0335 0.3028 1.0000
9.750 1.2502 0.05049 0.04124 -0.0290 0.2962 1.0000
10.000 1.2658 0.05055 0.04136 -0.0275 0.2862 1.0000
10.250 1.2100 0.05716 0.04823 -0.0246 0.2795 1.0000
10.500 1.2072 0.05905 0.05024 -0.0233 0.2693 1.0000
10.750 1.1365 0.07015 0.06147 -0.0246 0.2594 1.0000
11.000 1.0830 0.08096 0.07231 -0.0276 0.2455 1.0000
11.250 1.0586 0.08796 0.07934 -0.0297 0.2318 1.0000
11.750 1.0376 0.09771 0.08920 -0.0324 0.2076 1.0000
12.000 1.0399 0.10033 0.09190 -0.0329 0.1973 1.0000
12.250 1.0594 0.09953 0.09123 -0.0320 0.1882 1.0000
12.500 1.0976 0.09505 0.08685 -0.0294 0.1779 1.0000
12.750 1.1267 0.09229 0.08397 -0.0272 0.1642 1.0000
13.000 1.1322 0.09412 0.08569 -0.0270 0.1517 1.0000
13.250 1.1280 0.09800 0.08956 -0.0277 0.1413 1.0000
13.500 1.1300 0.10069 0.09217 -0.0279 0.1312 1.0000
13.750 1.1280 0.10433 0.09583 -0.0286 0.1224 1.0000
14.000 1.1229 0.10884 0.10040 -0.0299 0.1155 1.0000
14.250 1.1186 0.11330 0.10495 -0.0314 0.1092 1.0000
14.500 1.1210 0.11635 0.10799 -0.0321 0.1037 1.0000
14.750 1.1035 0.12401 0.11589 -0.0354 0.0994 1.0000
15.000 1.1025 0.12799 0.11991 -0.0370 0.0948 1.0000
15.250 1.0987 0.13273 0.12471 -0.0389 0.0912 1.0000
15.500 1.0587 0.14660 0.13880 -0.0459 0.0891 1.0000
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Polar data table (+)
Polar graphs
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