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HOBIE (hobie-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HOBIE (hobie-il)
Reynolds number: 50,000
Max Cl/Cd: 40.78 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobie-il-50000.txt
Download as CSV file: xf-hobie-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3762   0.10275   0.09582  -0.0216   1.0000   0.2369
  -7.750  -0.3517   0.09695   0.08999  -0.0202   1.0000   0.2459
  -7.500  -0.3774   0.09767   0.09092  -0.0200   1.0000   0.2516
  -7.250  -0.3567   0.09270   0.08593  -0.0186   1.0000   0.2638
  -7.000  -0.3528   0.08963   0.08294  -0.0173   1.0000   0.2730
  -6.750  -0.3763   0.08978   0.08331  -0.0168   1.0000   0.2812
  -6.500  -0.3614   0.08563   0.07917  -0.0143   1.0000   0.2931
  -6.250  -0.3603   0.08286   0.07647  -0.0129   1.0000   0.3023
  -5.750  -0.3797   0.08013   0.07399  -0.0120   1.0000   0.3259
  -5.500  -0.3718   0.07676   0.07068  -0.0086   1.0000   0.3390
  -5.250  -0.3748   0.07465   0.06866  -0.0066   1.0000   0.3541
  -4.750  -0.3807   0.07031   0.06449  -0.0023   1.0000   0.3874
  -4.500  -0.3792   0.06776   0.06199   0.0010   1.0000   0.4045
  -4.250  -0.3785   0.06542   0.05971   0.0039   1.0000   0.4222
  -4.000  -0.3824   0.06369   0.05804   0.0059   1.0000   0.4488
  -3.750  -0.3795   0.06121   0.05560   0.0107   1.0000   0.4729
  -3.500  -0.2343   0.03994   0.03208  -0.0528   1.0000   0.1893
  -3.250  -0.2066   0.03670   0.02842  -0.0550   1.0000   0.1868
  -3.000  -0.1787   0.03413   0.02534  -0.0567   1.0000   0.1886
  -2.750  -0.1504   0.03183   0.02256  -0.0579   1.0000   0.1882
  -2.500  -0.1230   0.03008   0.02031  -0.0587   1.0000   0.1908
  -2.250  -0.1002   0.02902   0.01912  -0.0586   1.0000   0.1975
  -2.000  -0.0761   0.02802   0.01782  -0.0586   1.0000   0.2029
  -1.750  -0.0516   0.02711   0.01657  -0.0585   1.0000   0.2083
  -1.500  -0.0301   0.02651   0.01592  -0.0581   1.0000   0.2157
  -1.250  -0.0088   0.02609   0.01542  -0.0576   1.0000   0.2291
  -1.000   0.0136   0.02574   0.01498  -0.0573   1.0000   0.2470
  -0.750   0.0376   0.02533   0.01460  -0.0573   1.0000   0.2729
  -0.500   0.0630   0.02475   0.01439  -0.0574   1.0000   0.3492
  -0.250   0.0866   0.02296   0.01430  -0.0562   1.0000   0.6525
   0.000   0.1013   0.02264   0.01418  -0.0552   0.9988   1.0000
   0.250   0.1564   0.02393   0.01492  -0.0616   0.9838   1.0000
   0.500   0.2053   0.02501   0.01565  -0.0668   0.9681   1.0000
   0.750   0.2510   0.02598   0.01636  -0.0713   0.9516   1.0000
   1.000   0.2950   0.02688   0.01707  -0.0753   0.9352   1.0000
   1.250   0.3376   0.02772   0.01777  -0.0788   0.9188   1.0000
   1.500   0.3787   0.02851   0.01845  -0.0820   0.9026   1.0000
   1.750   0.4182   0.02926   0.01912  -0.0847   0.8867   1.0000
   2.000   0.4572   0.02995   0.01977  -0.0871   0.8708   1.0000
   2.250   0.4969   0.03054   0.02033  -0.0894   0.8547   1.0000
   2.500   0.5368   0.03104   0.02083  -0.0915   0.8387   1.0000
   2.750   0.5770   0.03143   0.02126  -0.0934   0.8229   1.0000
   3.000   0.6171   0.03172   0.02161  -0.0951   0.8073   1.0000
   3.250   0.6563   0.03196   0.02194  -0.0964   0.7920   1.0000
   3.500   0.6913   0.03224   0.02229  -0.0970   0.7768   1.0000
   3.750   0.7258   0.03244   0.02258  -0.0973   0.7614   1.0000
   4.000   0.7602   0.03254   0.02280  -0.0973   0.7459   1.0000
   4.250   0.7915   0.03277   0.02317  -0.0969   0.7307   1.0000
   4.500   0.8206   0.03314   0.02368  -0.0964   0.7156   1.0000
   4.750   0.8505   0.03340   0.02409  -0.0957   0.7001   1.0000
   5.000   0.8814   0.03353   0.02441  -0.0950   0.6843   1.0000
   5.250   0.9131   0.03357   0.02463  -0.0941   0.6682   1.0000
   5.500   0.9326   0.03426   0.02548  -0.0923   0.6481   1.0000
   5.750   0.9728   0.03268   0.02409  -0.0903   0.6245   1.0000
   6.000   1.0029   0.03166   0.02321  -0.0877   0.5976   1.0000
   6.250   1.0337   0.03058   0.02225  -0.0851   0.5704   1.0000
   6.500   1.0624   0.02950   0.02128  -0.0823   0.5400   1.0000
   6.750   1.0887   0.02824   0.02000  -0.0789   0.5034   1.0000
   7.000   1.1053   0.02739   0.01910  -0.0747   0.4569   1.0000
   7.250   1.1117   0.02726   0.01885  -0.0696   0.3928   1.0000
   7.500   1.1045   0.02832   0.01931  -0.0634   0.2872   1.0000
   7.750   1.1006   0.03126   0.02117  -0.0589   0.2118   1.0000
   8.000   1.1150   0.03402   0.02351  -0.0568   0.1744   1.0000
   8.250   1.1325   0.03591   0.02539  -0.0551   0.1523   1.0000
   8.500   1.1566   0.03791   0.02732  -0.0540   0.1382   1.0000
   8.750   1.1818   0.04009   0.02951  -0.0532   0.1265   1.0000
   9.000   1.2134   0.04299   0.03250  -0.0531   0.1190   1.0000
   9.250   1.2386   0.04589   0.03561  -0.0524   0.1129   1.0000
   9.500   1.2606   0.04939   0.03927  -0.0517   0.1080   1.0000
   9.750   1.2735   0.05312   0.04354  -0.0499   0.1063   1.0000
  10.000   1.2816   0.05722   0.04815  -0.0479   0.1057   1.0000
  10.250   1.2828   0.06142   0.05283  -0.0457   0.1053   1.0000
  10.500   1.2772   0.06568   0.05753  -0.0433   0.1050   1.0000
  10.750   1.2660   0.07006   0.06228  -0.0409   0.1051   1.0000
  11.000   1.2491   0.07442   0.06695  -0.0386   0.1056   1.0000
  11.250   1.2278   0.07879   0.07156  -0.0364   0.1064   1.0000
  11.500   1.2042   0.08367   0.07662  -0.0355   0.1073   1.0000
  11.750   1.1822   0.08915   0.08226  -0.0357   0.1082   1.0000
  12.000   1.1639   0.09519   0.08840  -0.0369   0.1091   1.0000
  12.250   1.0448   0.11567   0.10906  -0.0537   0.1201   1.0000
  12.500   1.0348   0.12421   0.11761  -0.0575   0.1230   1.0000
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