Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Rhode St. Genese 30 (rhodesg30-il) Reynolds number: 500,000 Max Cl/Cd: 88.74 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg30-il-500000.txt Download as CSV file: xf-rhodesg30-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4169 0.10493 0.10261 -0.0252 1.0000 0.0356
-11.500 -0.4272 0.09804 0.09574 -0.0279 1.0000 0.0299
-11.250 -0.7658 0.03022 0.02699 -0.0618 1.0000 0.0205
-11.000 -0.7472 0.03037 0.02713 -0.0595 1.0000 0.0196
-10.750 -0.7568 0.02721 0.02363 -0.0552 1.0000 0.0187
-10.500 -0.7295 0.02587 0.02161 -0.0552 0.9984 0.0164
-10.250 -0.6982 0.02436 0.02000 -0.0565 0.9958 0.0153
-10.000 -0.6693 0.02234 0.01769 -0.0578 0.9928 0.0148
-9.750 -0.6396 0.02085 0.01598 -0.0587 0.9893 0.0144
-9.500 -0.6079 0.01961 0.01456 -0.0599 0.9864 0.0142
-9.250 -0.5747 0.01848 0.01329 -0.0613 0.9841 0.0142
-9.000 -0.5445 0.01744 0.01215 -0.0621 0.9802 0.0143
-8.750 -0.5116 0.01657 0.01119 -0.0632 0.9760 0.0143
-8.500 -0.4763 0.01570 0.01024 -0.0649 0.9730 0.0147
-8.250 -0.4395 0.01495 0.00939 -0.0668 0.9709 0.0152
-8.000 -0.4077 0.01442 0.00877 -0.0675 0.9663 0.0154
-7.750 -0.3744 0.01394 0.00820 -0.0685 0.9618 0.0156
-7.500 -0.3388 0.01350 0.00766 -0.0699 0.9579 0.0158
-7.250 -0.3069 0.01309 0.00717 -0.0705 0.9521 0.0160
-7.000 -0.2763 0.01263 0.00661 -0.0708 0.9457 0.0167
-6.750 -0.2447 0.01205 0.00592 -0.0714 0.9402 0.0174
-6.500 -0.2187 0.01142 0.00517 -0.0709 0.9313 0.0184
-6.250 -0.1863 0.01202 0.00592 -0.0714 0.9238 0.0230
-6.000 -0.1615 0.01122 0.00501 -0.0706 0.9143 0.0357
-5.750 -0.1336 0.01130 0.00503 -0.0702 0.9055 0.0383
-5.500 -0.1048 0.01156 0.00522 -0.0700 0.8971 0.0401
-5.250 -0.0781 0.01174 0.00541 -0.0696 0.8873 0.0418
-5.000 -0.0497 0.01254 0.00626 -0.0694 0.8782 0.0450
-4.750 -0.0220 0.01353 0.00722 -0.0690 0.8678 0.0483
-4.500 0.0026 0.01276 0.00637 -0.0684 0.8564 0.0502
-4.250 0.0281 0.01246 0.00608 -0.0679 0.8449 0.0524
-4.000 0.0542 0.01239 0.00600 -0.0675 0.8339 0.0549
-3.750 0.0807 0.01245 0.00601 -0.0670 0.8223 0.0574
-3.500 0.1068 0.01229 0.00574 -0.0665 0.8099 0.0599
-3.250 0.1322 0.01148 0.00490 -0.0659 0.7973 0.0613
-3.000 0.1584 0.01114 0.00450 -0.0653 0.7836 0.0611
-2.750 0.1846 0.01090 0.00419 -0.0647 0.7687 0.0606
-2.500 0.2104 0.01061 0.00383 -0.0641 0.7526 0.0605
-2.250 0.2357 0.01030 0.00347 -0.0634 0.7353 0.0606
-2.000 0.2608 0.01003 0.00313 -0.0626 0.7169 0.0610
-1.750 0.2857 0.00980 0.00283 -0.0619 0.6968 0.0617
-1.500 0.3106 0.00965 0.00261 -0.0612 0.6743 0.0624
-1.250 0.3352 0.00956 0.00244 -0.0604 0.6489 0.0631
-1.000 0.3597 0.00953 0.00230 -0.0596 0.6197 0.0639
-0.750 0.3834 0.00958 0.00220 -0.0586 0.5809 0.0645
-0.500 0.4058 0.00975 0.00214 -0.0575 0.5200 0.0652
-0.250 0.4274 0.01005 0.00214 -0.0563 0.4553 0.0659
0.000 0.4511 0.01025 0.00217 -0.0555 0.4220 0.0667
0.250 0.4760 0.01038 0.00220 -0.0550 0.4042 0.0684
0.500 0.5016 0.01048 0.00224 -0.0545 0.3917 0.0698
0.750 0.5273 0.01058 0.00230 -0.0541 0.3821 0.0708
1.000 0.5531 0.01067 0.00235 -0.0537 0.3746 0.0737
1.250 0.5790 0.01074 0.00243 -0.0532 0.3683 0.0815
1.500 0.5895 0.00906 0.00263 -0.0504 0.3625 0.7546
1.750 0.6703 0.00889 0.00289 -0.0618 0.3493 1.0000
2.000 0.6940 0.00907 0.00301 -0.0610 0.3428 1.0000
2.250 0.7182 0.00922 0.00314 -0.0603 0.3381 1.0000
2.500 0.7427 0.00935 0.00327 -0.0597 0.3331 1.0000
2.750 0.7663 0.00955 0.00342 -0.0588 0.3264 1.0000
3.000 0.7911 0.00965 0.00353 -0.0583 0.3193 1.0000
3.250 0.8151 0.00982 0.00368 -0.0576 0.3127 1.0000
3.500 0.8397 0.00995 0.00384 -0.0570 0.3068 1.0000
3.750 0.8641 0.01009 0.00398 -0.0563 0.2990 1.0000
4.000 0.8887 0.01023 0.00413 -0.0558 0.2902 1.0000
4.250 0.9129 0.01039 0.00428 -0.0551 0.2785 1.0000
4.500 0.9371 0.01056 0.00441 -0.0545 0.2565 1.0000
4.750 0.9513 0.01158 0.00484 -0.0525 0.1516 1.0000
5.000 0.9659 0.01269 0.00559 -0.0505 0.0885 1.0000
5.250 0.9831 0.01356 0.00622 -0.0489 0.0534 1.0000
5.500 1.0051 0.01397 0.00670 -0.0480 0.0503 1.0000
5.750 1.0259 0.01448 0.00725 -0.0469 0.0472 1.0000
6.000 1.0455 0.01509 0.00790 -0.0456 0.0442 1.0000
6.250 1.0637 0.01578 0.00866 -0.0441 0.0420 1.0000
6.500 1.0844 0.01622 0.00917 -0.0430 0.0407 1.0000
6.750 1.1038 0.01676 0.00977 -0.0418 0.0391 1.0000
7.000 1.1217 0.01737 0.01044 -0.0404 0.0372 1.0000
7.250 1.1379 0.01807 0.01119 -0.0387 0.0354 1.0000
7.500 1.1466 0.01925 0.01243 -0.0359 0.0333 1.0000
7.750 1.1590 0.02010 0.01337 -0.0337 0.0319 1.0000
8.000 1.1749 0.02060 0.01394 -0.0320 0.0307 1.0000
8.250 1.1874 0.02123 0.01464 -0.0298 0.0293 1.0000
8.500 1.1995 0.02189 0.01533 -0.0276 0.0277 1.0000
8.750 1.2090 0.02272 0.01619 -0.0253 0.0263 1.0000
9.000 1.2022 0.02481 0.01835 -0.0210 0.0246 1.0000
9.250 1.2181 0.02528 0.01890 -0.0198 0.0238 1.0000
9.500 1.2313 0.02598 0.01969 -0.0183 0.0225 1.0000
9.750 1.2424 0.02686 0.02065 -0.0168 0.0213 1.0000
10.000 1.2520 0.02789 0.02172 -0.0153 0.0205 1.0000
10.250 1.2584 0.02920 0.02306 -0.0137 0.0195 1.0000
10.500 1.2550 0.03157 0.02550 -0.0114 0.0186 1.0000
10.750 1.2658 0.03263 0.02668 -0.0105 0.0180 1.0000
11.000 1.2750 0.03390 0.02804 -0.0096 0.0170 1.0000
11.250 1.2812 0.03553 0.02976 -0.0087 0.0164 1.0000
11.500 1.2875 0.03719 0.03149 -0.0080 0.0158 1.0000
11.750 1.2936 0.03892 0.03329 -0.0076 0.0152 1.0000
12.000 1.2947 0.04128 0.03571 -0.0071 0.0147 1.0000
12.250 1.2921 0.04414 0.03867 -0.0065 0.0144 1.0000
12.500 1.2904 0.04704 0.04170 -0.0062 0.0138 1.0000
12.750 1.2910 0.04979 0.04459 -0.0061 0.0135 1.0000
13.000 1.2899 0.05278 0.04772 -0.0062 0.0133 1.0000
13.250 1.2898 0.05578 0.05084 -0.0066 0.0130 1.0000
13.500 1.2873 0.05918 0.05437 -0.0072 0.0126 1.0000
13.750 1.2859 0.06255 0.05785 -0.0082 0.0123 1.0000
14.000 1.2844 0.06609 0.06148 -0.0095 0.0120 1.0000
14.250 1.2818 0.06990 0.06539 -0.0109 0.0117 1.0000
14.500 1.2796 0.07377 0.06936 -0.0126 0.0115 1.0000
14.750 1.2756 0.07799 0.07365 -0.0144 0.0112 1.0000
15.000 1.2697 0.08255 0.07830 -0.0162 0.0110 1.0000
15.250 1.2585 0.08795 0.08384 -0.0181 0.0108 1.0000
15.750 1.2309 0.10037 0.09662 -0.0233 0.0105 1.0000
16.000 1.2184 0.10661 0.10302 -0.0262 0.0106 1.0000
16.250 1.2067 0.11307 0.10964 -0.0296 0.0105 1.0000
16.500 1.1935 0.11993 0.11665 -0.0333 0.0104 1.0000
16.750 1.1766 0.12773 0.12462 -0.0375 0.0104 1.0000
17.000 1.1596 0.13589 0.13295 -0.0421 0.0103 1.0000
17.250 1.1381 0.14529 0.14251 -0.0474 0.0104 1.0000
17.500 1.1176 0.15503 0.15241 -0.0531 0.0105 1.0000
17.750 1.0834 0.16928 0.16684 -0.0614 0.0106 1.0000
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Polar data table (+)
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