Rhode St. Genese 32 (rhodesg32-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 32 (rhodesg32-il) Reynolds number: 500,000 Max Cl/Cd: 89.68 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg32-il-500000-n5.txt Download as CSV file: xf-rhodesg32-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8739 0.03426 0.03108 -0.0884 0.9975 0.0273
-14.000 -0.8574 0.03164 0.02822 -0.0902 0.9900 0.0279
-13.750 -0.8229 0.03216 0.02882 -0.0908 0.9863 0.0282
-13.500 -0.7901 0.03229 0.02897 -0.0917 0.9817 0.0285
-13.250 -0.7575 0.03243 0.02912 -0.0924 0.9754 0.0289
-13.000 -0.7267 0.03175 0.02837 -0.0940 0.9695 0.0293
-12.750 -0.6997 0.03021 0.02665 -0.0958 0.9621 0.0300
-12.500 -0.6831 0.02647 0.02241 -0.0978 0.9524 0.0313
-12.250 -0.6602 0.02387 0.01936 -0.0992 0.9442 0.0322
-12.000 -0.6303 0.02346 0.01892 -0.0999 0.9354 0.0327
-11.750 -0.5990 0.02328 0.01870 -0.1007 0.9281 0.0331
-11.500 -0.5726 0.02298 0.01835 -0.1006 0.9193 0.0334
-11.000 -0.5234 0.02207 0.01723 -0.0998 0.9039 0.0344
-10.750 -0.5007 0.02132 0.01630 -0.0991 0.8956 0.0350
-10.500 -0.4800 0.02045 0.01525 -0.0981 0.8871 0.0357
-10.000 -0.4368 0.01861 0.01299 -0.0962 0.8726 0.0369
-9.750 -0.4135 0.01799 0.01217 -0.0953 0.8649 0.0374
-9.500 -0.3908 0.01724 0.01134 -0.0945 0.8571 0.0379
-9.250 -0.3666 0.01680 0.01082 -0.0937 0.8487 0.0383
-9.000 -0.3421 0.01637 0.01033 -0.0930 0.8406 0.0387
-8.750 -0.3173 0.01597 0.00984 -0.0923 0.8330 0.0391
-8.500 -0.2924 0.01554 0.00934 -0.0916 0.8249 0.0396
-8.250 -0.2675 0.01515 0.00884 -0.0909 0.8154 0.0401
-8.000 -0.2427 0.01474 0.00833 -0.0901 0.8031 0.0406
-7.750 -0.2178 0.01436 0.00785 -0.0894 0.7898 0.0413
-7.500 -0.1926 0.01401 0.00738 -0.0886 0.7770 0.0420
-7.250 -0.1675 0.01367 0.00692 -0.0879 0.7631 0.0426
-7.000 -0.1425 0.01336 0.00648 -0.0871 0.7477 0.0430
-6.750 -0.1175 0.01308 0.00608 -0.0863 0.7305 0.0434
-6.500 -0.0929 0.01272 0.00561 -0.0855 0.7136 0.0439
-6.250 -0.0687 0.01236 0.00516 -0.0847 0.6953 0.0445
-6.000 -0.0442 0.01215 0.00486 -0.0839 0.6755 0.0451
-5.750 -0.0194 0.01199 0.00461 -0.0831 0.6566 0.0458
-5.500 0.0053 0.01188 0.00440 -0.0823 0.6361 0.0465
-5.250 0.0299 0.01178 0.00419 -0.0815 0.6135 0.0473
-5.000 0.0542 0.01170 0.00399 -0.0806 0.5877 0.0482
-4.750 0.0778 0.01165 0.00378 -0.0796 0.5529 0.0489
-4.500 0.1001 0.01171 0.00361 -0.0784 0.4997 0.0496
-4.250 0.1197 0.01203 0.00355 -0.0768 0.4153 0.0503
-4.000 0.1430 0.01213 0.00346 -0.0759 0.3797 0.0508
-3.750 0.1677 0.01210 0.00334 -0.0752 0.3627 0.0515
-3.500 0.1922 0.01196 0.00314 -0.0744 0.3523 0.0527
-3.250 0.2178 0.01188 0.00304 -0.0739 0.3450 0.0541
-2.750 0.2693 0.01180 0.00289 -0.0729 0.3349 0.0567
-2.500 0.2953 0.01176 0.00283 -0.0724 0.3313 0.0580
-2.250 0.3212 0.01174 0.00279 -0.0719 0.3278 0.0592
-2.000 0.3471 0.01175 0.00276 -0.0715 0.3247 0.0603
-1.500 0.3987 0.01170 0.00270 -0.0705 0.3199 0.0653
-1.250 0.4248 0.01169 0.00269 -0.0701 0.3181 0.0682
-1.000 0.4510 0.01169 0.00269 -0.0697 0.3163 0.0713
-0.750 0.4768 0.01167 0.00270 -0.0692 0.3140 0.0794
-0.500 0.5017 0.01157 0.00276 -0.0687 0.3113 0.1377
-0.250 0.5271 0.01159 0.00282 -0.0682 0.3086 0.1608
0.250 0.5764 0.01151 0.00299 -0.0671 0.3048 0.2533
0.500 0.5914 0.01056 0.00314 -0.0650 0.3033 0.6336
0.750 0.6549 0.00997 0.00343 -0.0724 0.3004 0.9689
1.000 0.7098 0.01014 0.00356 -0.0784 0.2979 0.9979
1.250 0.7386 0.01027 0.00366 -0.0787 0.2960 1.0000
1.500 0.7615 0.01039 0.00376 -0.0777 0.2940 1.0000
1.750 0.7844 0.01052 0.00386 -0.0768 0.2923 1.0000
2.000 0.8072 0.01067 0.00399 -0.0758 0.2909 1.0000
2.250 0.8301 0.01082 0.00411 -0.0748 0.2895 1.0000
2.500 0.8527 0.01098 0.00426 -0.0739 0.2880 1.0000
2.750 0.8756 0.01115 0.00441 -0.0730 0.2867 1.0000
3.000 0.8994 0.01125 0.00454 -0.0722 0.2852 1.0000
3.250 0.9233 0.01134 0.00464 -0.0715 0.2823 1.0000
3.500 0.9468 0.01145 0.00476 -0.0708 0.2786 1.0000
3.750 0.9699 0.01160 0.00490 -0.0699 0.2755 1.0000
4.000 0.9926 0.01176 0.00505 -0.0691 0.2730 1.0000
4.250 1.0155 0.01192 0.00521 -0.0682 0.2700 1.0000
4.500 1.0393 0.01204 0.00536 -0.0676 0.2669 1.0000
4.750 1.0626 0.01217 0.00552 -0.0668 0.2635 1.0000
5.000 1.0853 0.01233 0.00568 -0.0660 0.2591 1.0000
5.250 1.1079 0.01250 0.00585 -0.0652 0.2538 1.0000
5.500 1.1304 0.01266 0.00601 -0.0644 0.2442 1.0000
5.750 1.1524 0.01285 0.00620 -0.0635 0.2346 1.0000
6.000 1.1617 0.01373 0.00666 -0.0607 0.1655 1.0000
6.250 1.1758 0.01436 0.00720 -0.0586 0.1491 1.0000
6.500 1.1921 0.01478 0.00760 -0.0568 0.1411 1.0000
6.750 1.2075 0.01523 0.00804 -0.0548 0.1340 1.0000
7.000 1.2245 0.01560 0.00843 -0.0532 0.1283 1.0000
7.250 1.2404 0.01605 0.00888 -0.0514 0.1226 1.0000
7.500 1.2570 0.01646 0.00931 -0.0499 0.1179 1.0000
7.750 1.2738 0.01688 0.00975 -0.0484 0.1126 1.0000
8.000 1.2883 0.01744 0.01029 -0.0466 0.1055 1.0000
8.250 1.3039 0.01794 0.01079 -0.0451 0.0958 1.0000
8.500 1.3074 0.01915 0.01176 -0.0420 0.0617 1.0000
8.750 1.3164 0.02006 0.01263 -0.0398 0.0548 1.0000
9.000 1.3284 0.02080 0.01342 -0.0381 0.0511 1.0000
9.250 1.3401 0.02159 0.01425 -0.0364 0.0486 1.0000
9.500 1.3503 0.02250 0.01520 -0.0347 0.0464 1.0000
9.750 1.3597 0.02349 0.01623 -0.0330 0.0443 1.0000
10.000 1.3723 0.02429 0.01710 -0.0317 0.0430 1.0000
10.250 1.3830 0.02524 0.01812 -0.0303 0.0416 1.0000
10.500 1.3922 0.02634 0.01928 -0.0289 0.0400 1.0000
10.750 1.3998 0.02759 0.02058 -0.0275 0.0386 1.0000
11.000 1.4050 0.02908 0.02212 -0.0261 0.0371 1.0000
11.250 1.4139 0.03034 0.02346 -0.0251 0.0362 1.0000
11.500 1.4220 0.03170 0.02490 -0.0241 0.0349 1.0000
11.750 1.4279 0.03331 0.02658 -0.0232 0.0336 1.0000
12.000 1.4323 0.03513 0.02845 -0.0224 0.0323 1.0000
12.250 1.4344 0.03722 0.03061 -0.0216 0.0312 1.0000
12.500 1.4378 0.03929 0.03276 -0.0211 0.0303 1.0000
12.750 1.4415 0.04141 0.03497 -0.0208 0.0290 1.0000
13.000 1.4428 0.04387 0.03751 -0.0205 0.0278 1.0000
13.250 1.4419 0.04665 0.04036 -0.0204 0.0268 1.0000
13.500 1.4386 0.04985 0.04365 -0.0206 0.0259 1.0000
13.750 1.4377 0.05286 0.04676 -0.0208 0.0249 1.0000
14.000 1.4340 0.05631 0.05031 -0.0213 0.0240 1.0000
14.250 1.4289 0.06008 0.05417 -0.0219 0.0232 1.0000
14.500 1.4219 0.06420 0.05839 -0.0228 0.0223 1.0000
14.750 1.4130 0.06870 0.06297 -0.0239 0.0217 1.0000
15.000 1.4053 0.07314 0.06752 -0.0250 0.0211 1.0000
15.250 1.3975 0.07767 0.07216 -0.0263 0.0204 1.0000
15.500 1.3892 0.08231 0.07689 -0.0277 0.0197 1.0000
15.750 1.3811 0.08693 0.08160 -0.0290 0.0190 1.0000
16.000 1.3729 0.09159 0.08632 -0.0305 0.0183 1.0000
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Polar data table (+)
Polar graphs
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