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HOBIE (hobie-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HOBIE (hobie-il)
Reynolds number: 100,000
Max Cl/Cd: 60.3 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hobie-il-100000-n5.txt
Download as CSV file: xf-hobie-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HOBIE                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3656   0.09063   0.08566  -0.0342   1.0000   0.0338
  -8.250  -0.3684   0.08744   0.08255  -0.0347   1.0000   0.0340
  -8.000  -0.3735   0.08438   0.07957  -0.0348   1.0000   0.0341
  -7.750  -0.3817   0.08152   0.07682  -0.0344   1.0000   0.0340
  -7.500  -0.3890   0.07834   0.07374  -0.0347   1.0000   0.0339
  -7.250  -0.3946   0.07484   0.07032  -0.0358   1.0000   0.0340
  -7.000  -0.3995   0.07104   0.06659  -0.0374   1.0000   0.0340
  -6.750  -0.4028   0.06686   0.06246  -0.0397   1.0000   0.0343
  -6.500  -0.4033   0.06199   0.05760  -0.0431   1.0000   0.0351
  -6.250  -0.3792   0.05052   0.04588  -0.0571   0.9952   0.0368
  -6.000  -0.3395   0.03490   0.02881  -0.0741   0.9876   0.0397
  -5.750  -0.3077   0.03328   0.02713  -0.0768   0.9817   0.0430
  -5.500  -0.2720   0.03035   0.02370  -0.0804   0.9766   0.0476
  -5.250  -0.2373   0.02720   0.01960  -0.0834   0.9700   0.0536
  -5.000  -0.2043   0.02573   0.01804  -0.0854   0.9643   0.0586
  -4.750  -0.1684   0.02424   0.01600  -0.0875   0.9582   0.0645
  -4.500  -0.1355   0.02261   0.01417  -0.0891   0.9514   0.0696
  -4.250  -0.0986   0.02152   0.01284  -0.0912   0.9458   0.0747
  -4.000  -0.0647   0.02060   0.01163  -0.0924   0.9377   0.0788
  -3.750  -0.0260   0.01969   0.01045  -0.0945   0.9323   0.0807
  -3.500   0.0044   0.01870   0.00946  -0.0951   0.9231   0.0847
  -3.250   0.0388   0.01800   0.00870  -0.0964   0.9161   0.0878
  -3.000   0.0708   0.01740   0.00801  -0.0970   0.9072   0.0897
  -2.750   0.1027   0.01689   0.00740  -0.0977   0.8982   0.0920
  -2.500   0.1363   0.01642   0.00683  -0.0985   0.8899   0.0949
  -2.250   0.1662   0.01601   0.00639  -0.0988   0.8798   0.0985
  -2.000   0.1999   0.01561   0.00596  -0.0998   0.8727   0.1042
  -1.750   0.2283   0.01534   0.00568  -0.0997   0.8623   0.1121
  -1.500   0.2591   0.01498   0.00542  -0.1002   0.8538   0.1350
  -1.250   0.2892   0.01458   0.00532  -0.1006   0.8445   0.2194
  -1.000   0.3176   0.01434   0.00520  -0.1005   0.8336   0.2761
  -0.750   0.3473   0.01411   0.00511  -0.1006   0.8229   0.3381
  -0.500   0.3772   0.01392   0.00495  -0.1007   0.8118   0.3813
   0.000   0.4307   0.01329   0.00489  -0.0998   0.7869   0.5554
   0.500   0.4927   0.01240   0.00463  -0.0996   0.7600   1.0000
   0.750   0.5199   0.01249   0.00457  -0.0992   0.7451   1.0000
   1.000   0.5469   0.01259   0.00454  -0.0987   0.7304   1.0000
   1.250   0.5739   0.01271   0.00454  -0.0982   0.7164   1.0000
   1.500   0.6005   0.01284   0.00459  -0.0977   0.7024   1.0000
   1.750   0.6269   0.01299   0.00467  -0.0972   0.6883   1.0000
   2.000   0.6531   0.01314   0.00476  -0.0967   0.6739   1.0000
   2.250   0.6792   0.01330   0.00488  -0.0962   0.6593   1.0000
   2.500   0.7052   0.01346   0.00501  -0.0956   0.6441   1.0000
   2.750   0.7311   0.01364   0.00515  -0.0950   0.6284   1.0000
   3.000   0.7569   0.01382   0.00531  -0.0944   0.6129   1.0000
   3.250   0.7825   0.01402   0.00548  -0.0938   0.5971   1.0000
   3.500   0.8081   0.01423   0.00568  -0.0932   0.5816   1.0000
   3.750   0.8337   0.01447   0.00591  -0.0926   0.5670   1.0000
   4.000   0.8589   0.01472   0.00616  -0.0920   0.5517   1.0000
   4.250   0.8836   0.01499   0.00642  -0.0912   0.5338   1.0000
   4.500   0.9080   0.01528   0.00669  -0.0904   0.5153   1.0000
   4.750   0.9322   0.01560   0.00700  -0.0896   0.4969   1.0000
   5.000   0.9566   0.01592   0.00738  -0.0888   0.4808   1.0000
   5.250   0.9805   0.01626   0.00777  -0.0880   0.4628   1.0000
   5.500   1.0032   0.01664   0.00814  -0.0869   0.4401   1.0000
   5.750   1.0255   0.01708   0.00857  -0.0858   0.4176   1.0000
   6.000   1.0484   0.01750   0.00907  -0.0849   0.3980   1.0000
   6.250   1.0700   0.01795   0.00959  -0.0838   0.3704   1.0000
   6.500   1.0884   0.01854   0.01005  -0.0822   0.3195   1.0000
   6.750   1.1029   0.01951   0.01068  -0.0802   0.2487   1.0000
   7.000   1.1146   0.02093   0.01168  -0.0780   0.1997   1.0000
   7.250   1.1237   0.02274   0.01288  -0.0758   0.0963   1.0000
   7.500   1.1334   0.02450   0.01442  -0.0734   0.0709   1.0000
   7.750   1.1451   0.02598   0.01595  -0.0712   0.0588   1.0000
   8.000   1.1562   0.02741   0.01750  -0.0689   0.0506   1.0000
   8.250   1.1667   0.02879   0.01900  -0.0666   0.0445   1.0000
   8.500   1.1749   0.03029   0.02059  -0.0641   0.0403   1.0000
   8.750   1.1837   0.03159   0.02205  -0.0615   0.0367   1.0000
   9.000   1.1909   0.03303   0.02359  -0.0589   0.0340   1.0000
   9.250   1.1972   0.03458   0.02521  -0.0565   0.0317   1.0000
   9.500   1.2014   0.03663   0.02730  -0.0540   0.0296   1.0000
   9.750   1.2128   0.03832   0.02916  -0.0522   0.0281   1.0000
  10.000   1.2253   0.04020   0.03119  -0.0505   0.0267   1.0000
  10.250   1.2369   0.04203   0.03316  -0.0490   0.0250   1.0000
  10.500   1.2467   0.04388   0.03513  -0.0475   0.0236   1.0000
  10.750   1.2555   0.04592   0.03726  -0.0461   0.0225   1.0000
  11.000   1.2675   0.04860   0.04006  -0.0449   0.0216   1.0000
  11.250   1.2791   0.05183   0.04351  -0.0438   0.0210   1.0000
  11.500   1.2831   0.05463   0.04667  -0.0422   0.0205   1.0000
  11.750   1.2828   0.05765   0.05001  -0.0407   0.0199   1.0000
  12.000   1.2792   0.06086   0.05352  -0.0394   0.0194   1.0000
  12.250   1.2731   0.06436   0.05730  -0.0385   0.0189   1.0000
  12.500   1.2651   0.06812   0.06132  -0.0381   0.0185   1.0000
  12.750   1.2548   0.07233   0.06578  -0.0381   0.0183   1.0000
  13.000   1.2425   0.07696   0.07067  -0.0388   0.0181   1.0000
  13.250   1.2276   0.08220   0.07617  -0.0401   0.0180   1.0000
  13.500   1.2107   0.08805   0.08227  -0.0422   0.0180   1.0000
  13.750   1.1917   0.09462   0.08908  -0.0451   0.0181   1.0000
  14.000   1.1711   0.10194   0.09663  -0.0490   0.0182   1.0000
  14.250   1.1489   0.11023   0.10513  -0.0540   0.0183   1.0000
  14.500   1.1257   0.11962   0.11473  -0.0600   0.0186   1.0000
  14.750   1.1011   0.13043   0.12570  -0.0672   0.0190   1.0000
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