Rhode St. Genese 32 (rhodesg32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Rhode St. Genese 32 (rhodesg32-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.04 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg32-il-1000000.txt Download as CSV file: xf-rhodesg32-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.0709 0.03398 0.03130 -0.1046 1.0000 0.0226
-16.750 -1.0861 0.03157 0.02873 -0.1024 1.0000 0.0228
-16.500 -1.0930 0.03019 0.02723 -0.0987 1.0000 0.0230
-16.250 -1.0921 0.02876 0.02567 -0.0961 1.0000 0.0232
-16.000 -1.0939 0.02724 0.02406 -0.0929 1.0000 0.0237
-15.750 -1.0834 0.02662 0.02342 -0.0905 1.0000 0.0241
-15.500 -1.0692 0.02635 0.02317 -0.0883 1.0000 0.0245
-15.250 -1.0590 0.02610 0.02291 -0.0853 1.0000 0.0248
-15.000 -1.0299 0.02587 0.02267 -0.0858 0.9990 0.0253
-14.750 -0.9969 0.02559 0.02236 -0.0870 0.9974 0.0260
-14.500 -0.9666 0.02459 0.02122 -0.0884 0.9950 0.0266
-14.250 -0.9345 0.02404 0.02057 -0.0896 0.9925 0.0270
-14.000 -0.9094 0.02246 0.01884 -0.0906 0.9879 0.0278
-13.750 -0.8760 0.02224 0.01864 -0.0918 0.9852 0.0282
-13.500 -0.8402 0.02237 0.01882 -0.0931 0.9831 0.0287
-13.250 -0.8100 0.02220 0.01864 -0.0935 0.9781 0.0291
-13.000 -0.7769 0.02215 0.01856 -0.0944 0.9741 0.0297
-12.750 -0.7431 0.02155 0.01787 -0.0960 0.9711 0.0304
-12.500 -0.7125 0.02083 0.01702 -0.0970 0.9657 0.0310
-12.250 -0.6793 0.02055 0.01665 -0.0981 0.9604 0.0315
-12.000 -0.6523 0.01888 0.01479 -0.0991 0.9535 0.0323
-11.750 -0.6215 0.01870 0.01460 -0.0997 0.9452 0.0327
-11.500 -0.5912 0.01866 0.01453 -0.1001 0.9374 0.0331
-11.250 -0.5650 0.01836 0.01417 -0.0997 0.9287 0.0336
-11.000 -0.5387 0.01828 0.01403 -0.0993 0.9206 0.0341
-10.750 -0.5145 0.01792 0.01358 -0.0985 0.9126 0.0347
-10.500 -0.4912 0.01738 0.01291 -0.0977 0.9054 0.0353
-10.250 -0.4674 0.01705 0.01247 -0.0968 0.8978 0.0360
-10.000 -0.4430 0.01671 0.01199 -0.0960 0.8908 0.0364
-9.750 -0.4228 0.01545 0.01056 -0.0948 0.8840 0.0371
-9.500 -0.3988 0.01492 0.00996 -0.0941 0.8777 0.0377
-9.250 -0.3732 0.01474 0.00976 -0.0935 0.8717 0.0382
-9.000 -0.3478 0.01454 0.00953 -0.0928 0.8647 0.0387
-8.750 -0.3228 0.01419 0.00909 -0.0921 0.8573 0.0392
-8.500 -0.2976 0.01384 0.00868 -0.0914 0.8491 0.0398
-8.250 -0.2724 0.01346 0.00821 -0.0906 0.8411 0.0404
-8.000 -0.2470 0.01306 0.00774 -0.0900 0.8326 0.0410
-7.750 -0.2212 0.01281 0.00740 -0.0893 0.8242 0.0417
-7.500 -0.1951 0.01262 0.00714 -0.0887 0.8138 0.0421
-7.250 -0.1690 0.01245 0.00689 -0.0881 0.8036 0.0424
-7.000 -0.1461 0.01132 0.00566 -0.0872 0.7919 0.0435
-6.750 -0.1207 0.01098 0.00528 -0.0865 0.7783 0.0441
-6.500 -0.0951 0.01077 0.00502 -0.0858 0.7637 0.0447
-6.250 -0.0695 0.01059 0.00476 -0.0852 0.7477 0.0454
-6.000 -0.0441 0.01046 0.00455 -0.0844 0.7294 0.0462
-5.750 -0.0190 0.01030 0.00430 -0.0837 0.7097 0.0469
-5.500 0.0061 0.01015 0.00405 -0.0829 0.6874 0.0476
-5.250 0.0309 0.01005 0.00384 -0.0821 0.6642 0.0483
-5.000 0.0562 0.00999 0.00367 -0.0813 0.6425 0.0488
-4.750 0.0817 0.00997 0.00356 -0.0807 0.6198 0.0492
-4.500 0.1043 0.00955 0.00303 -0.0795 0.5946 0.0505
-4.250 0.1279 0.00949 0.00283 -0.0786 0.5568 0.0516
-4.000 0.1483 0.00976 0.00277 -0.0771 0.4710 0.0526
-3.750 0.1684 0.01011 0.00278 -0.0755 0.3890 0.0535
-3.500 0.1930 0.01016 0.00271 -0.0748 0.3643 0.0545
-3.250 0.2185 0.01016 0.00263 -0.0742 0.3518 0.0555
-3.000 0.2448 0.01013 0.00256 -0.0738 0.3448 0.0565
-2.750 0.2710 0.01013 0.00252 -0.0733 0.3388 0.0572
-2.500 0.2965 0.01003 0.00237 -0.0727 0.3334 0.0589
-2.250 0.3228 0.00992 0.00227 -0.0723 0.3309 0.0611
-2.000 0.3493 0.00988 0.00222 -0.0719 0.3281 0.0630
-1.750 0.3758 0.00986 0.00219 -0.0715 0.3253 0.0648
-1.500 0.4021 0.00988 0.00218 -0.0711 0.3221 0.0664
-1.250 0.4278 0.00990 0.00217 -0.0706 0.3180 0.0695
-1.000 0.4542 0.00987 0.00216 -0.0703 0.3159 0.0749
-0.500 0.5061 0.00966 0.00222 -0.0695 0.3130 0.1625
-0.250 0.5322 0.00961 0.00225 -0.0691 0.3108 0.1919
0.000 0.5558 0.00932 0.00232 -0.0684 0.3088 0.3269
0.250 0.5754 0.00875 0.00241 -0.0670 0.3069 0.5746
0.500 0.5893 0.00815 0.00253 -0.0641 0.3051 0.8154
1.000 0.7164 0.00833 0.00297 -0.0796 0.2995 0.9963
1.250 0.7603 0.00842 0.00305 -0.0832 0.2984 1.0000
1.500 0.7834 0.00851 0.00312 -0.0822 0.2974 1.0000
1.750 0.8065 0.00860 0.00321 -0.0813 0.2964 1.0000
2.000 0.8298 0.00869 0.00329 -0.0804 0.2950 1.0000
2.250 0.8533 0.00878 0.00337 -0.0795 0.2934 1.0000
2.500 0.8767 0.00887 0.00345 -0.0786 0.2913 1.0000
2.750 0.8998 0.00899 0.00355 -0.0777 0.2886 1.0000
3.000 0.9220 0.00917 0.00370 -0.0767 0.2853 1.0000
3.250 0.9453 0.00929 0.00382 -0.0758 0.2835 1.0000
3.500 0.9697 0.00936 0.00391 -0.0752 0.2823 1.0000
3.750 0.9942 0.00942 0.00399 -0.0746 0.2803 1.0000
4.000 1.0185 0.00951 0.00408 -0.0740 0.2781 1.0000
4.250 1.0426 0.00960 0.00418 -0.0733 0.2757 1.0000
4.500 1.0662 0.00972 0.00430 -0.0726 0.2728 1.0000
4.750 1.0887 0.00990 0.00445 -0.0717 0.2690 1.0000
5.000 1.1136 0.00995 0.00454 -0.0713 0.2656 1.0000
5.250 1.1379 0.01004 0.00463 -0.0707 0.2607 1.0000
5.500 1.1609 0.01019 0.00475 -0.0700 0.2550 1.0000
5.750 1.1845 0.01030 0.00488 -0.0693 0.2485 1.0000
6.000 1.2068 0.01049 0.00502 -0.0685 0.2361 1.0000
6.250 1.2129 0.01157 0.00565 -0.0650 0.1619 1.0000
6.750 1.2465 0.01255 0.00650 -0.0615 0.1360 1.0000
7.000 1.2649 0.01293 0.00686 -0.0601 0.1281 1.0000
7.250 1.2818 0.01330 0.00720 -0.0583 0.1206 1.0000
7.500 1.2982 0.01365 0.00754 -0.0565 0.1132 1.0000
7.750 1.3128 0.01410 0.00794 -0.0544 0.1026 1.0000
8.000 1.3221 0.01485 0.00850 -0.0516 0.0719 1.0000
8.250 1.3290 0.01574 0.00926 -0.0485 0.0552 1.0000
8.500 1.3429 0.01629 0.00982 -0.0466 0.0509 1.0000
8.750 1.3566 0.01687 0.01041 -0.0447 0.0481 1.0000
9.000 1.3683 0.01757 0.01113 -0.0427 0.0450 1.0000
9.500 1.3987 0.01863 0.01227 -0.0398 0.0420 1.0000
10.000 1.4215 0.02021 0.01391 -0.0364 0.0381 1.0000
10.250 1.4353 0.02090 0.01465 -0.0351 0.0370 1.0000
10.500 1.4495 0.02158 0.01538 -0.0339 0.0357 1.0000
10.750 1.4618 0.02242 0.01624 -0.0326 0.0342 1.0000
11.000 1.4706 0.02351 0.01735 -0.0311 0.0325 1.0000
11.250 1.4809 0.02454 0.01844 -0.0299 0.0312 1.0000
11.500 1.4935 0.02544 0.01939 -0.0289 0.0300 1.0000
11.750 1.5033 0.02658 0.02056 -0.0278 0.0286 1.0000
12.000 1.5099 0.02801 0.02202 -0.0267 0.0273 1.0000
12.250 1.5164 0.02951 0.02358 -0.0256 0.0262 1.0000
12.500 1.5265 0.03076 0.02489 -0.0249 0.0249 1.0000
12.750 1.5322 0.03243 0.02660 -0.0241 0.0239 1.0000
13.000 1.5349 0.03445 0.02866 -0.0234 0.0228 1.0000
13.250 1.5377 0.03654 0.03082 -0.0227 0.0218 1.0000
13.500 1.5413 0.03862 0.03298 -0.0223 0.0212 1.0000
13.750 1.5433 0.04097 0.03539 -0.0221 0.0204 1.0000
14.000 1.5425 0.04370 0.03819 -0.0219 0.0196 1.0000
14.250 1.5358 0.04721 0.04178 -0.0219 0.0188 1.0000
14.500 1.5302 0.05072 0.04538 -0.0221 0.0184 1.0000
14.750 1.5272 0.05404 0.04879 -0.0225 0.0181 1.0000
15.000 1.5225 0.05763 0.05248 -0.0230 0.0176 1.0000
15.250 1.5156 0.06163 0.05658 -0.0237 0.0172 1.0000
15.500 1.5063 0.06605 0.06110 -0.0247 0.0170 1.0000
15.750 1.4952 0.07081 0.06595 -0.0258 0.0166 1.0000
16.000 1.4830 0.07581 0.07105 -0.0270 0.0164 1.0000
16.250 1.4687 0.08117 0.07651 -0.0284 0.0161 1.0000
16.500 1.4528 0.08676 0.08218 -0.0299 0.0157 1.0000
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Polar data table (+)
Polar graphs
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