Rhode St. Genese 32 (rhodesg32-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Rhode St. Genese 32 (rhodesg32-il) Reynolds number: 50,000 Max Cl/Cd: 24.3 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg32-il-50000.txt Download as CSV file: xf-rhodesg32-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3400 0.10574 0.09908 -0.0248 1.0000 0.2625
-9.750 -0.3057 0.09997 0.09326 -0.0229 1.0000 0.2744
-9.500 -0.3461 0.10127 0.09478 -0.0204 1.0000 0.2795
-9.250 -0.3182 0.09641 0.08990 -0.0186 1.0000 0.2920
-9.000 -0.3630 0.09778 0.09150 -0.0147 1.0000 0.2966
-8.750 -0.3374 0.09333 0.08704 -0.0129 1.0000 0.3095
-8.500 -0.3875 0.09474 0.08868 -0.0080 1.0000 0.3138
-8.250 -0.3645 0.09068 0.08461 -0.0062 1.0000 0.3274
-8.000 -0.4248 0.09232 0.08649 -0.0023 1.0000 0.3318
-7.750 -0.4020 0.08850 0.08268 0.0011 1.0000 0.3466
-7.500 -0.3994 0.08597 0.08021 0.0041 1.0000 0.3591
-7.250 -0.4108 0.08428 0.07861 0.0073 1.0000 0.3729
-7.000 -0.4180 0.08252 0.07693 0.0107 1.0000 0.3905
-6.750 -0.4228 0.08080 0.07528 0.0144 1.0000 0.4116
-6.500 -0.4467 0.08001 0.07460 0.0178 1.0000 0.4350
-6.250 -0.4286 0.07724 0.07187 0.0227 1.0000 0.4635
-6.000 -0.4270 0.07543 0.07012 0.0277 1.0000 0.4982
-5.750 -0.4332 0.07414 0.06892 0.0333 1.0000 0.5378
-5.500 -0.3735 0.07075 0.06548 0.0368 1.0000 0.6196
-5.250 -0.0609 0.05692 0.05103 0.0047 1.0000 0.9297
-5.000 -0.1051 0.05782 0.05210 0.0138 1.0000 0.9066
-4.750 -0.3498 0.04892 0.04150 -0.0230 1.0000 0.2303
-4.500 -0.3233 0.04573 0.03772 -0.0249 1.0000 0.2097
-4.250 -0.3034 0.04339 0.03518 -0.0251 1.0000 0.2022
-4.000 -0.2498 0.04103 0.03198 -0.0309 0.9885 0.1922
-3.750 -0.1967 0.03951 0.02992 -0.0362 0.9737 0.1929
-3.500 -0.1454 0.03820 0.02815 -0.0408 0.9585 0.1934
-3.250 -0.0939 0.03708 0.02664 -0.0451 0.9424 0.1951
-3.000 -0.0433 0.03608 0.02562 -0.0493 0.9256 0.2037
-2.750 0.0115 0.03526 0.02447 -0.0536 0.9081 0.2123
-2.500 0.0567 0.03439 0.02361 -0.0561 0.8885 0.2233
-2.250 0.1088 0.03355 0.02274 -0.0596 0.8677 0.2464
-2.000 0.1644 0.03214 0.02166 -0.0632 0.8475 0.2932
-1.750 0.2687 0.02839 0.01993 -0.0737 0.8303 1.0000
-1.500 0.3380 0.02764 0.01878 -0.0792 0.8098 1.0000
-1.250 0.3787 0.02718 0.01809 -0.0799 0.7821 1.0000
-1.000 0.4345 0.02624 0.01691 -0.0827 0.7608 1.0000
-0.750 0.4675 0.02591 0.01638 -0.0822 0.7336 1.0000
-0.500 0.5091 0.02536 0.01561 -0.0829 0.7132 1.0000
-0.250 0.5463 0.02504 0.01506 -0.0833 0.6946 1.0000
0.000 0.5700 0.02537 0.01522 -0.0821 0.6750 1.0000
0.250 0.6004 0.02553 0.01519 -0.0819 0.6606 1.0000
0.500 0.6242 0.02607 0.01561 -0.0812 0.6470 1.0000
0.750 0.6428 0.02695 0.01642 -0.0800 0.6347 1.0000
1.000 0.6689 0.02753 0.01689 -0.0797 0.6258 1.0000
1.250 0.6877 0.02851 0.01783 -0.0786 0.6165 1.0000
1.500 0.7103 0.02936 0.01861 -0.0781 0.6093 1.0000
1.750 0.7241 0.03068 0.01995 -0.0767 0.6014 1.0000
2.000 0.7543 0.03117 0.02035 -0.0769 0.5962 1.0000
2.250 0.7524 0.03353 0.02280 -0.0742 0.5889 1.0000
2.500 0.7654 0.03516 0.02444 -0.0731 0.5840 1.0000
2.750 0.7888 0.03624 0.02553 -0.0730 0.5806 1.0000
3.000 0.7779 0.03962 0.02898 -0.0702 0.5763 1.0000
3.250 0.7254 0.04610 0.03550 -0.0654 0.5721 1.0000
3.500 0.6745 0.05276 0.04213 -0.0619 0.5702 1.0000
3.750 0.6546 0.05733 0.04667 -0.0606 0.5700 1.0000
4.000 0.6398 0.06161 0.05094 -0.0599 0.5728 1.0000
4.250 0.6407 0.06497 0.05431 -0.0600 0.5763 1.0000
4.500 0.6510 0.06789 0.05725 -0.0604 0.5796 1.0000
4.750 0.6194 0.07333 0.06269 -0.0601 0.5941 1.0000
5.000 0.4709 0.08341 0.07286 -0.0591 0.7503 1.0000
5.250 0.4983 0.08643 0.07591 -0.0608 0.7447 1.0000
5.500 0.4998 0.08754 0.07703 -0.0593 0.7346 1.0000
5.750 0.5193 0.08996 0.07947 -0.0598 0.7233 1.0000
6.000 0.5405 0.09227 0.08181 -0.0603 0.7082 1.0000
6.250 0.5651 0.09493 0.08453 -0.0612 0.6934 1.0000
6.500 0.5913 0.09778 0.08744 -0.0622 0.6780 1.0000
6.750 0.5997 0.09940 0.08912 -0.0614 0.6628 1.0000
7.000 0.6107 0.10152 0.09130 -0.0611 0.6471 1.0000
7.250 0.6221 0.10394 0.09380 -0.0609 0.6313 1.0000
7.500 0.6376 0.10677 0.09671 -0.0611 0.6143 1.0000
7.750 0.6551 0.10989 0.09991 -0.0614 0.5970 1.0000
8.000 0.6636 0.11268 0.10276 -0.0613 0.5809 1.0000
8.250 0.6618 0.11523 0.10535 -0.0608 0.5678 1.0000
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Polar data table (+)
Polar graphs
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