HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HOBIESMO1.DAT (hobiesm-il) Reynolds number: 50,000 Max Cl/Cd: 41.46 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hobiesm-il-50000-n5.txt Download as CSV file: xf-hobiesm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HOBIESMO1.DAT
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3683 0.09789 0.09094 -0.0346 1.0000 0.0599
-8.500 -0.3689 0.09457 0.08771 -0.0353 1.0000 0.0594
-8.250 -0.3711 0.09131 0.08455 -0.0359 1.0000 0.0585
-8.000 -0.3758 0.08817 0.08152 -0.0362 1.0000 0.0577
-7.750 -0.3822 0.08502 0.07850 -0.0365 1.0000 0.0569
-7.500 -0.3866 0.08138 0.07498 -0.0379 1.0000 0.0562
-7.250 -0.3907 0.07745 0.07116 -0.0398 1.0000 0.0556
-7.000 -0.3939 0.07318 0.06697 -0.0422 1.0000 0.0550
-6.750 -0.3960 0.06821 0.06206 -0.0455 1.0000 0.0543
-6.500 -0.3953 0.06257 0.05640 -0.0493 1.0000 0.0539
-6.250 -0.3910 0.05597 0.04965 -0.0540 1.0000 0.0536
-6.000 -0.3821 0.05218 0.04573 -0.0555 1.0000 0.0549
-5.750 -0.3699 0.04859 0.04194 -0.0574 1.0000 0.0578
-5.500 -0.3522 0.04292 0.03575 -0.0615 1.0000 0.0609
-5.250 -0.3295 0.03725 0.02927 -0.0649 1.0000 0.0629
-5.000 -0.3060 0.03329 0.02461 -0.0665 1.0000 0.0650
-4.750 -0.2854 0.03150 0.02262 -0.0664 1.0000 0.0680
-4.500 -0.2622 0.02948 0.02017 -0.0665 1.0000 0.0726
-4.250 -0.2380 0.02792 0.01825 -0.0666 0.9995 0.0804
-4.000 -0.2005 0.02674 0.01680 -0.0693 0.9928 0.0957
-3.750 -0.1630 0.02551 0.01515 -0.0716 0.9859 0.1182
-3.500 -0.1268 0.02502 0.01460 -0.0740 0.9782 0.1482
-3.250 -0.0897 0.02459 0.01405 -0.0763 0.9706 0.1777
-3.000 -0.0552 0.02416 0.01342 -0.0780 0.9620 0.2033
-2.750 -0.0174 0.02372 0.01283 -0.0801 0.9548 0.2245
-2.500 0.0175 0.02336 0.01230 -0.0817 0.9459 0.2473
-2.250 0.0541 0.02301 0.01183 -0.0836 0.9378 0.2714
-2.000 0.0918 0.02269 0.01143 -0.0856 0.9298 0.3021
-1.750 0.1256 0.02239 0.01115 -0.0869 0.9205 0.3351
-1.500 0.1658 0.02203 0.01086 -0.0894 0.9137 0.3809
-1.250 0.1977 0.02172 0.01067 -0.0903 0.9037 0.4323
-1.000 0.2316 0.02128 0.01052 -0.0914 0.8950 0.5039
-0.750 0.2637 0.02052 0.01037 -0.0918 0.8872 0.6403
-0.500 0.3007 0.01988 0.01007 -0.0929 0.8769 1.0000
-0.250 0.3355 0.02002 0.00994 -0.0942 0.8672 1.0000
0.000 0.3722 0.02012 0.00981 -0.0957 0.8583 1.0000
0.250 0.4018 0.02030 0.00983 -0.0960 0.8466 1.0000
0.500 0.4321 0.02048 0.00987 -0.0964 0.8354 1.0000
0.750 0.4635 0.02063 0.00991 -0.0969 0.8247 1.0000
1.000 0.4977 0.02070 0.00990 -0.0977 0.8154 1.0000
1.250 0.5253 0.02091 0.01004 -0.0975 0.8030 1.0000
1.500 0.5531 0.02111 0.01020 -0.0973 0.7908 1.0000
1.750 0.5810 0.02131 0.01038 -0.0971 0.7787 1.0000
2.000 0.6092 0.02149 0.01058 -0.0969 0.7668 1.0000
2.250 0.6376 0.02166 0.01075 -0.0966 0.7550 1.0000
2.500 0.6664 0.02180 0.01091 -0.0964 0.7433 1.0000
2.750 0.6948 0.02194 0.01113 -0.0961 0.7314 1.0000
3.000 0.7210 0.02217 0.01141 -0.0955 0.7182 1.0000
3.250 0.7471 0.02240 0.01171 -0.0948 0.7049 1.0000
3.500 0.7732 0.02263 0.01203 -0.0942 0.6914 1.0000
3.750 0.7992 0.02286 0.01241 -0.0935 0.6778 1.0000
4.000 0.8253 0.02309 0.01276 -0.0928 0.6639 1.0000
4.250 0.8512 0.02333 0.01314 -0.0920 0.6498 1.0000
4.500 0.8771 0.02358 0.01353 -0.0912 0.6354 1.0000
4.750 0.9030 0.02384 0.01401 -0.0904 0.6208 1.0000
5.000 0.9288 0.02411 0.01446 -0.0896 0.6059 1.0000
5.250 0.9541 0.02442 0.01497 -0.0887 0.5907 1.0000
5.500 0.9778 0.02484 0.01564 -0.0876 0.5744 1.0000
5.750 0.9998 0.02480 0.01572 -0.0854 0.5467 1.0000
6.000 1.0133 0.02446 0.01522 -0.0813 0.4922 1.0000
6.250 1.0258 0.02474 0.01551 -0.0780 0.4380 1.0000
6.500 1.0343 0.02542 0.01596 -0.0743 0.3600 1.0000
6.750 1.0308 0.02750 0.01692 -0.0699 0.2013 1.0000
7.000 1.0234 0.03103 0.01921 -0.0666 0.0803 1.0000
7.250 1.0292 0.03329 0.02135 -0.0641 0.0654 1.0000
7.500 1.0328 0.03549 0.02357 -0.0615 0.0575 1.0000
7.750 1.0382 0.03733 0.02557 -0.0590 0.0515 1.0000
8.000 1.0412 0.03941 0.02777 -0.0566 0.0477 1.0000
8.250 1.0421 0.04180 0.03025 -0.0543 0.0456 1.0000
8.500 1.0495 0.04380 0.03244 -0.0522 0.0439 1.0000
8.750 1.0612 0.04571 0.03458 -0.0504 0.0421 1.0000
9.000 1.0778 0.04758 0.03672 -0.0488 0.0391 1.0000
9.250 1.0977 0.04966 0.03889 -0.0476 0.0358 1.0000
9.500 1.1444 0.05283 0.04214 -0.0481 0.0334 1.0000
9.750 1.1703 0.05582 0.04554 -0.0475 0.0327 1.0000
10.000 1.1863 0.05905 0.04917 -0.0464 0.0322 1.0000
10.250 1.1932 0.06230 0.05281 -0.0446 0.0319 1.0000
10.500 1.1933 0.06556 0.05643 -0.0427 0.0315 1.0000
10.750 1.1883 0.06894 0.06015 -0.0408 0.0311 1.0000
11.000 1.1799 0.07253 0.06406 -0.0394 0.0307 1.0000
11.250 1.1683 0.07644 0.06828 -0.0385 0.0305 1.0000
11.500 1.1552 0.08071 0.07282 -0.0383 0.0304 1.0000
11.750 1.1400 0.08544 0.07781 -0.0389 0.0304 1.0000
12.000 1.1235 0.09064 0.08325 -0.0403 0.0304 1.0000
12.250 1.1058 0.09642 0.08924 -0.0425 0.0306 1.0000
12.500 1.0878 0.10275 0.09576 -0.0456 0.0309 1.0000
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Polar data table (+)
Polar graphs
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