Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 30 (rhodesg30-il) Reynolds number: 500,000 Max Cl/Cd: 84.62 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg30-il-500000-n5.txt Download as CSV file: xf-rhodesg30-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Rhode St. Genese 30
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5227 0.08801 0.08553 -0.0346 1.0000 0.0059
-12.500 -0.5411 0.08047 0.07797 -0.0388 1.0000 0.0059
-12.250 -0.5591 0.07366 0.07116 -0.0426 1.0000 0.0058
-12.000 -0.5829 0.06600 0.06348 -0.0473 1.0000 0.0057
-11.750 -0.6153 0.05788 0.05537 -0.0528 1.0000 0.0055
-11.500 -0.6568 0.04389 0.04115 -0.0637 1.0000 0.0051
-11.250 -0.6691 0.03924 0.03627 -0.0639 1.0000 0.0052
-11.000 -0.6517 0.03481 0.03150 -0.0681 0.9926 0.0053
-10.750 -0.6309 0.03152 0.02789 -0.0708 0.9857 0.0054
-10.500 -0.6096 0.02903 0.02512 -0.0722 0.9783 0.0056
-10.250 -0.5848 0.02684 0.02267 -0.0736 0.9727 0.0057
-10.000 -0.5590 0.02490 0.02051 -0.0747 0.9667 0.0058
-9.750 -0.5319 0.02318 0.01857 -0.0758 0.9613 0.0058
-9.500 -0.5044 0.02168 0.01689 -0.0766 0.9539 0.0059
-9.250 -0.4753 0.02037 0.01544 -0.0776 0.9474 0.0060
-9.000 -0.4470 0.01925 0.01417 -0.0781 0.9383 0.0062
-8.750 -0.4194 0.01829 0.01307 -0.0785 0.9292 0.0063
-8.500 -0.3944 0.01709 0.01175 -0.0784 0.9200 0.0065
-8.250 -0.3705 0.01620 0.01076 -0.0779 0.9109 0.0067
-8.000 -0.3452 0.01554 0.00999 -0.0775 0.9028 0.0069
-7.750 -0.3204 0.01501 0.00939 -0.0769 0.8936 0.0071
-7.500 -0.2949 0.01459 0.00887 -0.0764 0.8850 0.0074
-7.250 -0.2692 0.01425 0.00844 -0.0758 0.8762 0.0077
-7.000 -0.2433 0.01390 0.00800 -0.0753 0.8682 0.0084
-6.750 -0.2172 0.01360 0.00758 -0.0748 0.8599 0.0087
-6.500 -0.1911 0.01340 0.00730 -0.0743 0.8504 0.0091
-6.250 -0.1651 0.01307 0.00685 -0.0738 0.8407 0.0096
-6.000 -0.1393 0.01267 0.00633 -0.0732 0.8300 0.0101
-5.750 -0.1137 0.01220 0.00574 -0.0726 0.8184 0.0107
-5.500 -0.0881 0.01172 0.00514 -0.0720 0.8060 0.0114
-5.250 -0.0632 0.01113 0.00439 -0.0713 0.7934 0.0127
-5.000 -0.0383 0.01061 0.00370 -0.0705 0.7797 0.0140
-4.750 -0.0130 0.01028 0.00324 -0.0698 0.7641 0.0154
-4.500 0.0130 0.01021 0.00321 -0.0693 0.7461 0.0324
-4.250 0.0398 0.01040 0.00333 -0.0688 0.7257 0.0379
-4.000 0.0666 0.01058 0.00337 -0.0684 0.7054 0.0400
-3.750 0.0934 0.01079 0.00357 -0.0681 0.6859 0.0418
-3.500 0.1197 0.01090 0.00360 -0.0677 0.6668 0.0431
-3.250 0.1459 0.01098 0.00359 -0.0672 0.6483 0.0445
-3.000 0.1722 0.01107 0.00361 -0.0668 0.6297 0.0458
-2.750 0.1985 0.01116 0.00360 -0.0664 0.6098 0.0466
-2.500 0.2239 0.01108 0.00342 -0.0658 0.5879 0.0468
-2.250 0.2491 0.01100 0.00324 -0.0652 0.5610 0.0469
-2.000 0.2730 0.01085 0.00295 -0.0644 0.5251 0.0473
-1.750 0.2959 0.01078 0.00268 -0.0635 0.4763 0.0477
-1.500 0.3192 0.01079 0.00251 -0.0627 0.4357 0.0483
-1.250 0.3438 0.01080 0.00240 -0.0621 0.4097 0.0489
-1.000 0.3691 0.01081 0.00234 -0.0616 0.3918 0.0495
-0.750 0.3947 0.01082 0.00229 -0.0612 0.3781 0.0503
-0.500 0.4205 0.01084 0.00227 -0.0607 0.3658 0.0509
-0.250 0.4463 0.01088 0.00226 -0.0604 0.3546 0.0517
0.000 0.4723 0.01092 0.00226 -0.0600 0.3455 0.0525
0.250 0.4985 0.01095 0.00227 -0.0597 0.3396 0.0535
0.500 0.5250 0.01097 0.00229 -0.0594 0.3351 0.0545
0.750 0.5513 0.01101 0.00233 -0.0591 0.3306 0.0560
1.000 0.5774 0.01109 0.00240 -0.0588 0.3251 0.0571
1.250 0.6036 0.01114 0.00244 -0.0585 0.3173 0.0582
1.500 0.6294 0.01124 0.00249 -0.0582 0.3107 0.0602
1.750 0.6559 0.01127 0.00256 -0.0579 0.3058 0.0628
2.000 0.6819 0.01135 0.00264 -0.0576 0.2993 0.0669
2.500 0.7165 0.00968 0.00302 -0.0539 0.2914 0.8334
3.000 0.8105 0.00985 0.00340 -0.0626 0.2747 1.0000
3.250 0.8346 0.01003 0.00353 -0.0619 0.2640 1.0000
3.500 0.8589 0.01020 0.00367 -0.0613 0.2520 1.0000
3.750 0.8826 0.01043 0.00384 -0.0607 0.2316 1.0000
4.000 0.8965 0.01152 0.00439 -0.0586 0.1372 1.0000
4.250 0.9178 0.01199 0.00477 -0.0576 0.1154 1.0000
4.500 0.9395 0.01244 0.00513 -0.0567 0.0963 1.0000
4.750 0.9577 0.01322 0.00566 -0.0552 0.0521 1.0000
5.000 0.9801 0.01359 0.00604 -0.0544 0.0453 1.0000
5.250 1.0030 0.01391 0.00640 -0.0537 0.0430 1.0000
5.500 1.0255 0.01427 0.00679 -0.0529 0.0409 1.0000
5.750 1.0475 0.01466 0.00721 -0.0520 0.0392 1.0000
6.000 1.0693 0.01506 0.00766 -0.0512 0.0381 1.0000
6.250 1.0905 0.01549 0.00814 -0.0502 0.0369 1.0000
6.500 1.1103 0.01602 0.00874 -0.0491 0.0351 1.0000
6.750 1.1315 0.01641 0.00917 -0.0482 0.0337 1.0000
7.000 1.1528 0.01676 0.00958 -0.0473 0.0326 1.0000
7.250 1.1733 0.01716 0.01003 -0.0464 0.0312 1.0000
7.500 1.1932 0.01759 0.01052 -0.0453 0.0297 1.0000
7.750 1.2120 0.01807 0.01103 -0.0442 0.0281 1.0000
8.000 1.2286 0.01867 0.01166 -0.0427 0.0262 1.0000
8.250 1.2440 0.01927 0.01233 -0.0409 0.0248 1.0000
8.500 1.2630 0.01957 0.01268 -0.0398 0.0235 1.0000
8.750 1.2800 0.01995 0.01312 -0.0383 0.0211 1.0000
9.000 1.2952 0.02043 0.01361 -0.0366 0.0182 1.0000
9.250 1.3084 0.02104 0.01422 -0.0347 0.0154 1.0000
9.500 1.3200 0.02175 0.01491 -0.0327 0.0127 1.0000
9.750 1.3302 0.02258 0.01579 -0.0306 0.0111 1.0000
10.000 1.3387 0.02352 0.01678 -0.0285 0.0098 1.0000
10.250 1.3456 0.02462 0.01795 -0.0264 0.0089 1.0000
10.500 1.3528 0.02575 0.01916 -0.0244 0.0083 1.0000
10.750 1.3592 0.02698 0.02050 -0.0226 0.0078 1.0000
11.000 1.3648 0.02835 0.02197 -0.0209 0.0074 1.0000
11.250 1.3692 0.02988 0.02359 -0.0193 0.0070 1.0000
11.500 1.3724 0.03160 0.02540 -0.0179 0.0067 1.0000
11.750 1.3724 0.03369 0.02759 -0.0166 0.0063 1.0000
12.000 1.3714 0.03604 0.03005 -0.0156 0.0060 1.0000
12.250 1.3714 0.03842 0.03255 -0.0149 0.0060 1.0000
12.500 1.3723 0.04085 0.03511 -0.0145 0.0056 1.0000
12.750 1.3708 0.04367 0.03805 -0.0144 0.0056 1.0000
13.000 1.3685 0.04673 0.04123 -0.0145 0.0053 1.0000
13.250 1.3669 0.04983 0.04445 -0.0149 0.0051 1.0000
13.500 1.3606 0.05367 0.04842 -0.0156 0.0051 1.0000
13.750 1.3555 0.05754 0.05241 -0.0165 0.0050 1.0000
14.000 1.3486 0.06185 0.05685 -0.0178 0.0048 1.0000
14.250 1.3437 0.06598 0.06109 -0.0191 0.0046 1.0000
14.500 1.3349 0.07088 0.06612 -0.0209 0.0046 1.0000
14.750 1.3259 0.07595 0.07130 -0.0228 0.0045 1.0000
15.000 1.3170 0.08106 0.07652 -0.0248 0.0045 1.0000
15.250 1.3035 0.08706 0.08263 -0.0272 0.0043 1.0000
15.500 1.2936 0.09252 0.08821 -0.0295 0.0043 1.0000
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Polar data table (+)
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