Rhode St. Genese 32 (rhodesg32-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 32 (rhodesg32-il) Reynolds number: 100,000 Max Cl/Cd: 48.26 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg32-il-100000-n5.txt Download as CSV file: xf-rhodesg32-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3714 0.08957 0.08461 -0.0446 1.0000 0.0602
-10.500 -0.3869 0.08714 0.08227 -0.0432 1.0000 0.0602
-10.250 -0.4026 0.08527 0.08049 -0.0407 1.0000 0.0600
-10.000 -0.4134 0.07922 0.07444 -0.0477 0.9926 0.0603
-9.750 -0.4005 0.07202 0.06714 -0.0565 0.9833 0.0602
-9.500 -0.3895 0.06585 0.06083 -0.0626 0.9739 0.0600
-9.250 -0.3809 0.05904 0.05378 -0.0685 0.9638 0.0599
-9.000 -0.3759 0.05123 0.04547 -0.0741 0.9538 0.0610
-8.750 -0.3469 0.04977 0.04405 -0.0757 0.9476 0.0621
-8.500 -0.3291 0.04498 0.03888 -0.0784 0.9395 0.0624
-8.250 -0.3068 0.04111 0.03464 -0.0805 0.9320 0.0628
-8.000 -0.2811 0.03849 0.03174 -0.0820 0.9253 0.0640
-7.750 -0.2578 0.03608 0.02903 -0.0827 0.9171 0.0655
-7.500 -0.2291 0.03330 0.02580 -0.0842 0.9117 0.0666
-7.250 -0.2087 0.03118 0.02328 -0.0835 0.9020 0.0672
-7.000 -0.1775 0.02907 0.02075 -0.0846 0.8965 0.0680
-6.750 -0.1555 0.02768 0.01901 -0.0837 0.8866 0.0693
-6.500 -0.1238 0.02632 0.01723 -0.0843 0.8806 0.0709
-6.250 -0.1007 0.02521 0.01589 -0.0834 0.8708 0.0718
-6.000 -0.0691 0.02389 0.01443 -0.0840 0.8643 0.0728
-5.750 -0.0455 0.02301 0.01346 -0.0830 0.8536 0.0738
-5.500 -0.0157 0.02211 0.01246 -0.0831 0.8456 0.0750
-5.250 0.0096 0.02142 0.01171 -0.0824 0.8350 0.0770
-5.000 0.0356 0.02077 0.01096 -0.0817 0.8242 0.0793
-4.750 0.0650 0.02007 0.01014 -0.0815 0.8146 0.0812
-4.500 0.0895 0.01951 0.00950 -0.0805 0.8017 0.0824
-4.250 0.1144 0.01889 0.00887 -0.0795 0.7882 0.0840
-4.000 0.1397 0.01834 0.00833 -0.0787 0.7750 0.0861
-3.750 0.1658 0.01789 0.00788 -0.0781 0.7627 0.0896
-3.500 0.1923 0.01750 0.00742 -0.0774 0.7499 0.0934
-3.250 0.2170 0.01714 0.00706 -0.0765 0.7351 0.0970
-3.000 0.2425 0.01682 0.00673 -0.0756 0.7192 0.1016
-2.750 0.2683 0.01655 0.00642 -0.0748 0.7018 0.1082
-2.500 0.2938 0.01631 0.00620 -0.0740 0.6826 0.1232
-2.250 0.3189 0.01608 0.00597 -0.0732 0.6610 0.1539
-2.000 0.3440 0.01579 0.00574 -0.0724 0.6373 0.1986
-1.750 0.3685 0.01538 0.00559 -0.0717 0.6108 0.2983
-1.500 0.3859 0.01439 0.00559 -0.0695 0.5824 0.6049
-1.250 0.4789 0.01402 0.00559 -0.0814 0.5210 0.9925
-1.000 0.5023 0.01434 0.00555 -0.0806 0.4854 1.0000
-0.750 0.5217 0.01465 0.00557 -0.0789 0.4613 1.0000
-0.500 0.5417 0.01496 0.00563 -0.0774 0.4446 1.0000
-0.250 0.5625 0.01526 0.00571 -0.0761 0.4325 1.0000
0.000 0.5838 0.01556 0.00582 -0.0748 0.4232 1.0000
0.250 0.6060 0.01583 0.00596 -0.0738 0.4155 1.0000
0.500 0.6284 0.01612 0.00611 -0.0728 0.4094 1.0000
0.750 0.6513 0.01642 0.00627 -0.0718 0.4044 1.0000
1.000 0.6749 0.01669 0.00647 -0.0711 0.3998 1.0000
1.250 0.6987 0.01697 0.00667 -0.0704 0.3960 1.0000
1.500 0.7228 0.01728 0.00690 -0.0697 0.3927 1.0000
1.750 0.7475 0.01762 0.00713 -0.0692 0.3899 1.0000
2.000 0.7724 0.01793 0.00739 -0.0687 0.3873 1.0000
2.250 0.7974 0.01824 0.00770 -0.0683 0.3848 1.0000
2.500 0.8224 0.01856 0.00801 -0.0679 0.3823 1.0000
2.750 0.8474 0.01890 0.00833 -0.0674 0.3795 1.0000
3.000 0.8721 0.01926 0.00866 -0.0670 0.3760 1.0000
3.500 0.9209 0.02001 0.00937 -0.0661 0.3685 1.0000
3.750 0.9445 0.02036 0.00977 -0.0655 0.3644 1.0000
4.000 0.9688 0.02073 0.01016 -0.0651 0.3610 1.0000
4.250 0.9938 0.02114 0.01056 -0.0648 0.3583 1.0000
4.500 1.0194 0.02159 0.01099 -0.0646 0.3556 1.0000
4.750 1.0429 0.02198 0.01149 -0.0641 0.3528 1.0000
5.000 1.0662 0.02239 0.01200 -0.0635 0.3499 1.0000
5.250 1.0901 0.02282 0.01255 -0.0631 0.3475 1.0000
5.500 1.1140 0.02327 0.01308 -0.0627 0.3449 1.0000
5.750 1.1379 0.02371 0.01356 -0.0623 0.3416 1.0000
6.000 1.1623 0.02418 0.01401 -0.0620 0.3375 1.0000
6.250 1.1799 0.02456 0.01462 -0.0605 0.3319 1.0000
6.500 1.1999 0.02492 0.01506 -0.0595 0.3260 1.0000
6.750 1.2223 0.02533 0.01544 -0.0588 0.3206 1.0000
7.000 1.2377 0.02571 0.01609 -0.0571 0.3145 1.0000
7.250 1.2559 0.02608 0.01655 -0.0558 0.3084 1.0000
7.500 1.2748 0.02646 0.01697 -0.0546 0.3027 1.0000
7.750 1.2877 0.02686 0.01762 -0.0525 0.2957 1.0000
8.000 1.3035 0.02721 0.01809 -0.0508 0.2894 1.0000
8.250 1.3167 0.02764 0.01870 -0.0489 0.2829 1.0000
8.500 1.3273 0.02805 0.01929 -0.0465 0.2749 1.0000
8.750 1.3349 0.02847 0.01989 -0.0436 0.2662 1.0000
9.000 1.3410 0.02891 0.02046 -0.0406 0.2560 1.0000
9.250 1.3473 0.02953 0.02133 -0.0379 0.2425 1.0000
9.500 1.3536 0.03027 0.02227 -0.0355 0.2181 1.0000
9.750 1.3503 0.03116 0.02298 -0.0322 0.1881 1.0000
10.000 1.3411 0.03285 0.02442 -0.0288 0.1710 1.0000
10.250 1.3327 0.03499 0.02648 -0.0261 0.1589 1.0000
10.500 1.3230 0.03750 0.02896 -0.0238 0.1498 1.0000
10.750 1.3175 0.03994 0.03150 -0.0222 0.1410 1.0000
11.000 1.3067 0.04300 0.03460 -0.0207 0.1342 1.0000
11.250 1.2995 0.04601 0.03777 -0.0198 0.1260 1.0000
11.500 1.2853 0.04990 0.04174 -0.0193 0.1200 1.0000
11.750 1.2753 0.05372 0.04574 -0.0192 0.1124 1.0000
12.000 1.2591 0.05850 0.05060 -0.0197 0.1069 1.0000
12.250 1.2458 0.06329 0.05555 -0.0206 0.1007 1.0000
12.500 1.2302 0.06866 0.06101 -0.0219 0.0948 1.0000
12.750 1.2175 0.07383 0.06628 -0.0233 0.0891 1.0000
13.000 1.2057 0.07902 0.07154 -0.0248 0.0834 1.0000
13.250 1.1962 0.08389 0.07645 -0.0263 0.0788 1.0000
13.500 1.1879 0.08862 0.08120 -0.0277 0.0744 1.0000
13.750 1.1807 0.09317 0.08572 -0.0291 0.0711 1.0000
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Polar data table (+)
Polar graphs
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