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HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HOBIESMO1.DAT (hobiesm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 130.71 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobiesm-il-1000000.txt
Download as CSV file: xf-hobiesm-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3226   0.07908   0.07759  -0.0368   1.0000   0.0109
  -9.500  -0.3313   0.07340   0.07193  -0.0381   1.0000   0.0107
  -9.250  -0.5919   0.02740   0.02502  -0.0847   0.9949   0.0078
  -9.000  -0.5603   0.02546   0.02284  -0.0879   0.9920   0.0080
  -8.750  -0.5354   0.01897   0.01562  -0.0935   0.9868   0.0087
  -8.500  -0.5019   0.01787   0.01440  -0.0956   0.9845   0.0091
  -8.250  -0.4688   0.01713   0.01356  -0.0974   0.9817   0.0096
  -8.000  -0.4385   0.01613   0.01241  -0.0985   0.9763   0.0101
  -7.750  -0.4050   0.01515   0.01127  -0.1002   0.9723   0.0107
  -7.500  -0.3722   0.01453   0.01052  -0.1016   0.9668   0.0113
  -7.250  -0.3407   0.01351   0.00930  -0.1028   0.9591   0.0119
  -7.000  -0.3113   0.01208   0.00771  -0.1038   0.9495   0.0131
  -6.750  -0.2808   0.01163   0.00719  -0.1045   0.9393   0.0140
  -6.500  -0.2526   0.01111   0.00654  -0.1047   0.9274   0.0149
  -6.250  -0.2256   0.01069   0.00600  -0.1045   0.9151   0.0157
  -6.000  -0.1988   0.01036   0.00556  -0.1042   0.9035   0.0163
  -5.750  -0.1728   0.00979   0.00484  -0.1039   0.8929   0.0172
  -5.500  -0.1470   0.00909   0.00398  -0.1035   0.8829   0.0187
  -5.250  -0.1204   0.00873   0.00353  -0.1032   0.8733   0.0199
  -5.000  -0.0934   0.00845   0.00316  -0.1029   0.8642   0.0212
  -4.750  -0.0664   0.00824   0.00285  -0.1027   0.8557   0.0225
  -4.500  -0.0392   0.00806   0.00260  -0.1024   0.8468   0.0234
  -4.250  -0.0121   0.00772   0.00216  -0.1022   0.8387   0.0271
  -4.000   0.0151   0.00747   0.00189  -0.1019   0.8303   0.0352
  -3.750   0.0418   0.00708   0.00166  -0.1017   0.8221   0.0769
  -3.250   0.0966   0.00687   0.00145  -0.1014   0.8056   0.1034
  -3.000   0.1241   0.00681   0.00135  -0.1012   0.7975   0.1120
  -2.750   0.1517   0.00674   0.00126  -0.1011   0.7888   0.1210
  -2.500   0.1791   0.00665   0.00118  -0.1010   0.7803   0.1332
  -2.250   0.2065   0.00658   0.00110  -0.1008   0.7715   0.1472
  -2.000   0.2340   0.00647   0.00104  -0.1007   0.7623   0.1686
  -1.750   0.2613   0.00638   0.00098  -0.1005   0.7531   0.1925
  -1.500   0.2886   0.00631   0.00094  -0.1003   0.7433   0.2176
  -1.250   0.3160   0.00623   0.00091  -0.1002   0.7330   0.2416
  -1.000   0.3434   0.00619   0.00088  -0.1000   0.7225   0.2656
  -0.750   0.3707   0.00615   0.00087  -0.0998   0.7116   0.2901
  -0.500   0.3978   0.00612   0.00086  -0.0996   0.6996   0.3167
  -0.250   0.4251   0.00609   0.00087  -0.0995   0.6872   0.3440
   0.000   0.4522   0.00607   0.00088  -0.0993   0.6743   0.3712
   0.250   0.4793   0.00605   0.00089  -0.0991   0.6610   0.4026
   0.500   0.5062   0.00601   0.00092  -0.0989   0.6471   0.4419
   0.750   0.5326   0.00593   0.00097  -0.0986   0.6329   0.5076
   1.000   0.5580   0.00571   0.00105  -0.0982   0.6187   0.6374
   1.250   0.5914   0.00502   0.00113  -0.0993   0.6038   1.0000
   1.500   0.6181   0.00513   0.00118  -0.0990   0.5893   1.0000
   1.750   0.6449   0.00525   0.00124  -0.0987   0.5751   1.0000
   2.000   0.6716   0.00537   0.00130  -0.0984   0.5608   1.0000
   2.250   0.6983   0.00550   0.00137  -0.0982   0.5469   1.0000
   2.500   0.7250   0.00563   0.00146  -0.0979   0.5332   1.0000
   2.750   0.7517   0.00576   0.00155  -0.0976   0.5194   1.0000
   3.000   0.7777   0.00595   0.00165  -0.0972   0.4974   1.0000
   3.250   0.8033   0.00617   0.00177  -0.0968   0.4726   1.0000
   3.500   0.8292   0.00637   0.00190  -0.0964   0.4489   1.0000
   3.750   0.8542   0.00667   0.00205  -0.0959   0.4164   1.0000
   4.000   0.8792   0.00695   0.00222  -0.0954   0.3850   1.0000
   4.250   0.9019   0.00748   0.00247  -0.0946   0.3266   1.0000
   4.500   0.9217   0.00832   0.00289  -0.0933   0.2396   1.0000
   4.750   0.9306   0.01039   0.00396  -0.0906   0.0448   1.0000
   5.000   0.9532   0.01101   0.00446  -0.0896   0.0206   1.0000
   5.250   0.9780   0.01133   0.00482  -0.0891   0.0175   1.0000
   5.500   1.0016   0.01179   0.00528  -0.0883   0.0144   1.0000
   5.750   1.0250   0.01228   0.00584  -0.0875   0.0129   1.0000
   6.000   1.0489   0.01267   0.00627  -0.0868   0.0119   1.0000
   6.250   1.0722   0.01311   0.00674  -0.0860   0.0110   1.0000
   6.500   1.0946   0.01363   0.00729  -0.0851   0.0101   1.0000
   6.750   1.1090   0.01497   0.00877  -0.0828   0.0091   1.0000
   7.000   1.1330   0.01527   0.00910  -0.0822   0.0087   1.0000
   7.250   1.1545   0.01580   0.00968  -0.0812   0.0082   1.0000
   7.500   1.1737   0.01653   0.01047  -0.0798   0.0078   1.0000
   7.750   1.1926   0.01726   0.01125  -0.0784   0.0075   1.0000
   8.000   1.2107   0.01803   0.01208  -0.0769   0.0072   1.0000
   8.250   1.2284   0.01881   0.01290  -0.0754   0.0069   1.0000
   8.500   1.2449   0.01966   0.01381  -0.0737   0.0067   1.0000
   8.750   1.2585   0.02078   0.01500  -0.0716   0.0065   1.0000
   9.000   1.2643   0.02336   0.01770  -0.0685   0.0061   1.0000
   9.250   1.2795   0.02477   0.01924  -0.0667   0.0059   1.0000
   9.500   1.2943   0.02593   0.02051  -0.0649   0.0058   1.0000
   9.750   1.3081   0.02740   0.02212  -0.0629   0.0056   1.0000
  10.000   1.3218   0.02962   0.02452  -0.0611   0.0055   1.0000
  10.250   1.3338   0.03238   0.02751  -0.0592   0.0055   1.0000
  10.500   1.3412   0.03492   0.03027  -0.0566   0.0054   1.0000
  10.750   1.3436   0.03761   0.03319  -0.0535   0.0053   1.0000
  11.000   1.3406   0.04071   0.03656  -0.0502   0.0053   1.0000
  11.250   1.3311   0.04423   0.04034  -0.0466   0.0054   1.0000
  11.500   1.3192   0.04760   0.04393  -0.0434   0.0055   1.0000
  11.750   1.2982   0.05208   0.04864  -0.0406   0.0057   1.0000
  12.000   1.2534   0.06318   0.06036  -0.0372   0.0074   1.0000
  12.250   1.2363   0.06734   0.06467  -0.0369   0.0073   1.0000
  12.500   1.2166   0.07230   0.06979  -0.0375   0.0073   1.0000
  12.750   1.1978   0.07755   0.07519  -0.0389   0.0073   1.0000
  13.000   1.1759   0.08392   0.08171  -0.0415   0.0073   1.0000
  13.250   1.1525   0.09126   0.08919  -0.0452   0.0074   1.0000
  13.500   1.1338   0.09828   0.09634  -0.0493   0.0073   1.0000
  13.750   1.1055   0.10844   0.10665  -0.0557   0.0076   1.0000
  14.000   1.0809   0.11888   0.11721  -0.0627   0.0078   1.0000
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