Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 30 (rhodesg30-il) Reynolds number: 200,000 Max Cl/Cd: 66.32 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg30-il-200000-n5.txt Download as CSV file: xf-rhodesg30-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4664 0.10138 0.09762 -0.0298 1.0000 0.0117
-12.500 -0.4690 0.09700 0.09326 -0.0315 1.0000 0.0116
-12.250 -0.4782 0.09120 0.08748 -0.0341 1.0000 0.0115
-12.000 -0.4875 0.08571 0.08200 -0.0366 1.0000 0.0114
-11.750 -0.5014 0.07954 0.07585 -0.0397 1.0000 0.0112
-11.500 -0.5147 0.07389 0.07023 -0.0426 1.0000 0.0111
-11.250 -0.5354 0.06743 0.06381 -0.0461 1.0000 0.0110
-11.000 -0.5625 0.06136 0.05784 -0.0493 1.0000 0.0108
-10.750 -0.5970 0.05055 0.04692 -0.0567 1.0000 0.0106
-10.500 -0.6143 0.04302 0.03908 -0.0589 1.0000 0.0104
-10.250 -0.6216 0.03957 0.03540 -0.0573 1.0000 0.0104
-10.000 -0.6154 0.03648 0.03203 -0.0571 0.9980 0.0104
-9.750 -0.5907 0.03341 0.02863 -0.0597 0.9922 0.0105
-9.500 -0.5641 0.03107 0.02599 -0.0616 0.9870 0.0107
-9.250 -0.5377 0.02920 0.02391 -0.0629 0.9815 0.0108
-9.000 -0.5091 0.02761 0.02212 -0.0643 0.9769 0.0110
-8.750 -0.4813 0.02626 0.02059 -0.0652 0.9717 0.0111
-8.500 -0.4521 0.02498 0.01908 -0.0662 0.9668 0.0116
-8.250 -0.4212 0.02366 0.01762 -0.0678 0.9634 0.0122
-8.000 -0.3951 0.02249 0.01627 -0.0681 0.9570 0.0129
-7.750 -0.3635 0.02154 0.01513 -0.0693 0.9525 0.0133
-7.500 -0.3308 0.02069 0.01410 -0.0704 0.9476 0.0137
-7.250 -0.3009 0.01995 0.01318 -0.0709 0.9402 0.0141
-7.000 -0.2662 0.01917 0.01220 -0.0723 0.9349 0.0146
-6.750 -0.2373 0.01849 0.01133 -0.0724 0.9265 0.0151
-6.500 -0.2046 0.01768 0.01032 -0.0733 0.9203 0.0160
-6.250 -0.1773 0.01657 0.00899 -0.0731 0.9117 0.0181
-6.000 -0.1449 0.01663 0.00908 -0.0739 0.9048 0.0209
-5.750 -0.1176 0.01620 0.00855 -0.0735 0.8954 0.0342
-5.500 -0.0880 0.01566 0.00779 -0.0735 0.8871 0.0392
-5.250 -0.0599 0.01596 0.00804 -0.0734 0.8769 0.0425
-5.000 -0.0326 0.01600 0.00797 -0.0730 0.8671 0.0449
-4.750 -0.0046 0.01610 0.00791 -0.0728 0.8576 0.0475
-4.500 0.0211 0.01595 0.00784 -0.0725 0.8463 0.0514
-4.250 0.0471 0.01579 0.00760 -0.0720 0.8344 0.0537
-4.000 0.0735 0.01581 0.00752 -0.0714 0.8211 0.0563
-3.750 0.0996 0.01561 0.00720 -0.0709 0.8065 0.0579
-3.500 0.1256 0.01505 0.00655 -0.0703 0.7924 0.0581
-3.250 0.1518 0.01460 0.00604 -0.0698 0.7796 0.0582
-3.000 0.1779 0.01419 0.00557 -0.0692 0.7661 0.0583
-2.750 0.2037 0.01378 0.00512 -0.0686 0.7517 0.0585
-2.500 0.2293 0.01342 0.00470 -0.0680 0.7361 0.0588
-2.250 0.2546 0.01310 0.00433 -0.0673 0.7190 0.0593
-2.000 0.2798 0.01284 0.00401 -0.0666 0.7003 0.0599
-1.750 0.3048 0.01264 0.00374 -0.0659 0.6803 0.0605
-1.500 0.3298 0.01250 0.00351 -0.0652 0.6588 0.0613
-1.250 0.3547 0.01241 0.00333 -0.0645 0.6359 0.0622
-1.000 0.3794 0.01236 0.00318 -0.0638 0.6116 0.0633
-0.750 0.4039 0.01237 0.00307 -0.0630 0.5839 0.0654
-0.500 0.4280 0.01242 0.00299 -0.0622 0.5503 0.0674
-0.250 0.4513 0.01255 0.00293 -0.0612 0.5107 0.0692
0.000 0.4744 0.01273 0.00291 -0.0602 0.4734 0.0704
0.500 0.5220 0.01307 0.00299 -0.0587 0.4275 0.0754
0.750 0.5463 0.01320 0.00308 -0.0580 0.4136 0.0816
1.000 0.5699 0.01313 0.00324 -0.0574 0.4020 0.1766
1.500 0.6500 0.01168 0.00377 -0.0630 0.3805 1.0000
1.750 0.6735 0.01193 0.00393 -0.0622 0.3742 1.0000
2.000 0.6979 0.01213 0.00410 -0.0616 0.3685 1.0000
2.250 0.7220 0.01236 0.00430 -0.0609 0.3627 1.0000
2.500 0.7458 0.01262 0.00450 -0.0602 0.3565 1.0000
2.750 0.7697 0.01283 0.00470 -0.0595 0.3464 1.0000
3.000 0.7933 0.01307 0.00491 -0.0588 0.3360 1.0000
3.250 0.8166 0.01334 0.00513 -0.0581 0.3270 1.0000
3.500 0.8411 0.01353 0.00535 -0.0575 0.3191 1.0000
3.750 0.8646 0.01380 0.00560 -0.0568 0.3115 1.0000
4.000 0.8890 0.01398 0.00585 -0.0563 0.3030 1.0000
4.250 0.9124 0.01424 0.00611 -0.0556 0.2950 1.0000
4.500 0.9368 0.01443 0.00638 -0.0551 0.2855 1.0000
4.750 0.9606 0.01466 0.00667 -0.0544 0.2756 1.0000
5.000 0.9840 0.01490 0.00695 -0.0538 0.2627 1.0000
5.250 1.0067 0.01518 0.00722 -0.0530 0.2376 1.0000
5.500 1.0199 0.01622 0.00775 -0.0511 0.1526 1.0000
5.750 1.0367 0.01713 0.00851 -0.0496 0.1199 1.0000
6.000 1.0548 0.01789 0.00919 -0.0483 0.0908 1.0000
6.500 1.0868 0.01962 0.01073 -0.0452 0.0550 1.0000
6.750 1.1043 0.02029 0.01150 -0.0437 0.0522 1.0000
7.000 1.1204 0.02103 0.01233 -0.0421 0.0500 1.0000
7.250 1.1342 0.02188 0.01327 -0.0402 0.0478 1.0000
7.500 1.1464 0.02276 0.01425 -0.0381 0.0455 1.0000
7.750 1.1600 0.02343 0.01506 -0.0362 0.0435 1.0000
8.000 1.1711 0.02423 0.01597 -0.0339 0.0411 1.0000
8.250 1.1804 0.02514 0.01699 -0.0316 0.0388 1.0000
8.500 1.1862 0.02631 0.01822 -0.0290 0.0365 1.0000
8.750 1.1853 0.02796 0.01995 -0.0260 0.0344 1.0000
9.000 1.1983 0.02877 0.02090 -0.0245 0.0328 1.0000
9.250 1.2077 0.02986 0.02212 -0.0229 0.0307 1.0000
9.500 1.2155 0.03109 0.02347 -0.0213 0.0284 1.0000
9.750 1.2208 0.03257 0.02502 -0.0198 0.0264 1.0000
10.000 1.2207 0.03456 0.02707 -0.0181 0.0247 1.0000
10.250 1.2288 0.03600 0.02868 -0.0170 0.0229 1.0000
10.500 1.2333 0.03781 0.03063 -0.0159 0.0210 1.0000
10.750 1.2388 0.03958 0.03249 -0.0152 0.0192 1.0000
11.000 1.2418 0.04168 0.03466 -0.0147 0.0180 1.0000
11.250 1.2423 0.04416 0.03725 -0.0142 0.0169 1.0000
11.500 1.2433 0.04670 0.03994 -0.0138 0.0159 1.0000
11.750 1.2431 0.04950 0.04286 -0.0137 0.0150 1.0000
12.000 1.2430 0.05238 0.04586 -0.0139 0.0143 1.0000
12.250 1.2414 0.05553 0.04913 -0.0143 0.0138 1.0000
12.500 1.2399 0.05884 0.05254 -0.0151 0.0131 1.0000
12.750 1.2359 0.06253 0.05633 -0.0158 0.0128 1.0000
13.000 1.2288 0.06679 0.06066 -0.0169 0.0122 1.0000
13.250 1.2256 0.07062 0.06465 -0.0178 0.0119 1.0000
13.500 1.2221 0.07460 0.06880 -0.0189 0.0116 1.0000
13.750 1.2182 0.07879 0.07316 -0.0202 0.0112 1.0000
14.000 1.2135 0.08327 0.07779 -0.0219 0.0107 1.0000
14.250 1.2086 0.08786 0.08253 -0.0238 0.0104 1.0000
14.500 1.2025 0.09272 0.08753 -0.0257 0.0101 1.0000
14.750 1.1957 0.09784 0.09280 -0.0280 0.0099 1.0000
15.000 1.1885 0.10312 0.09822 -0.0303 0.0098 1.0000
15.250 1.1802 0.10875 0.10397 -0.0330 0.0095 1.0000
15.500 1.1718 0.11447 0.10984 -0.0358 0.0094 1.0000
15.750 1.1623 0.12055 0.11605 -0.0389 0.0092 1.0000
16.000 1.1521 0.12693 0.12260 -0.0421 0.0093 1.0000
16.250 1.1417 0.13351 0.12931 -0.0456 0.0091 1.0000
16.500 1.1303 0.14054 0.13647 -0.0495 0.0090 1.0000
16.750 1.1160 0.14855 0.14466 -0.0540 0.0091 1.0000
17.000 1.0978 0.15809 0.15437 -0.0594 0.0091 1.0000
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Polar data table (+)
Polar graphs
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