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HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HOBIESMO1.DAT (hobiesm-il)
Reynolds number: 200,000
Max Cl/Cd: 81.49 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobiesm-il-200000.txt
Download as CSV file: xf-hobiesm-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3940   0.12370   0.11998  -0.0269   1.0000   0.0424
 -10.750  -0.3955   0.12108   0.11740  -0.0299   1.0000   0.0428
 -10.500  -0.3946   0.11796   0.11432  -0.0322   1.0000   0.0430
 -10.250  -0.3910   0.11212   0.10851  -0.0319   1.0000   0.0439
 -10.000  -0.3727   0.10926   0.10563  -0.0289   1.0000   0.0464
  -9.750  -0.3668   0.10649   0.10287  -0.0293   1.0000   0.0489
  -9.500  -0.3637   0.10348   0.09989  -0.0303   1.0000   0.0506
  -9.250  -0.3656   0.10053   0.09700  -0.0326   1.0000   0.0532
  -9.000  -0.2927   0.08538   0.08217  -0.0373   1.0000   0.0566
  -8.750  -0.2850   0.08253   0.07933  -0.0361   1.0000   0.0581
  -8.500  -0.2828   0.07961   0.07644  -0.0357   1.0000   0.0598
  -8.250  -0.2846   0.07657   0.07346  -0.0356   1.0000   0.0620
  -8.000  -0.2910   0.07368   0.07063  -0.0355   1.0000   0.0639
  -7.750  -0.3100   0.07159   0.06865  -0.0348   1.0000   0.0656
  -7.500  -0.3358   0.07099   0.06817  -0.0309   1.0000   0.0660
  -7.250  -0.3611   0.07067   0.06795  -0.0263   1.0000   0.0660
  -7.000  -0.3549   0.06222   0.05946  -0.0454   0.9929   0.0671
  -6.750  -0.3420   0.05757   0.05485  -0.0406   0.9897   0.0689
  -6.500  -0.3993   0.06435   0.06136  -0.0486   0.9958   0.0681
  -6.250  -0.3689   0.04231   0.03877  -0.0678   0.9892   0.0417
  -6.000  -0.3333   0.03179   0.02739  -0.0779   0.9844   0.0405
  -5.750  -0.2994   0.02547   0.02015  -0.0824   0.9796   0.0398
  -5.500  -0.2637   0.02201   0.01597  -0.0849   0.9748   0.0405
  -5.250  -0.2242   0.02026   0.01372  -0.0875   0.9713   0.0427
  -5.000  -0.1902   0.01794   0.01110  -0.0892   0.9667   0.0456
  -4.750  -0.1548   0.01676   0.00981  -0.0908   0.9613   0.0490
  -4.500  -0.1147   0.01579   0.00863  -0.0931   0.9578   0.0541
  -4.250  -0.0793   0.01489   0.00772  -0.0947   0.9524   0.0643
  -4.000  -0.0422   0.01404   0.00689  -0.0965   0.9471   0.0931
  -3.750  -0.0001   0.01369   0.00657  -0.0994   0.9438   0.1310
  -3.500   0.0355   0.01345   0.00626  -0.1010   0.9379   0.1513
  -3.250   0.0719   0.01323   0.00605  -0.1027   0.9321   0.1721
  -3.000   0.1115   0.01291   0.00569  -0.1050   0.9282   0.1930
  -2.750   0.1410   0.01258   0.00538  -0.1052   0.9194   0.2088
  -2.500   0.1772   0.01218   0.00503  -0.1067   0.9142   0.2306
  -2.250   0.2052   0.01189   0.00481  -0.1066   0.9047   0.2544
  -2.000   0.2369   0.01157   0.00456  -0.1071   0.8975   0.2870
  -1.750   0.2649   0.01132   0.00441  -0.1069   0.8881   0.3247
  -1.500   0.2923   0.01111   0.00430  -0.1066   0.8785   0.3652
  -1.250   0.3211   0.01085   0.00415  -0.1064   0.8703   0.4090
  -1.000   0.3463   0.01061   0.00407  -0.1057   0.8594   0.4605
  -0.750   0.3709   0.01028   0.00403  -0.1048   0.8489   0.5390
  -0.500   0.3914   0.00958   0.00400  -0.1027   0.8393   0.7392
  -0.250   0.4362   0.00914   0.00378  -0.1055   0.8299   1.0000
   0.000   0.4624   0.00920   0.00372  -0.1049   0.8183   1.0000
   0.250   0.4888   0.00927   0.00368  -0.1043   0.8069   1.0000
   0.500   0.5155   0.00933   0.00363  -0.1038   0.7956   1.0000
   0.750   0.5423   0.00939   0.00360  -0.1033   0.7844   1.0000
   1.000   0.5685   0.00947   0.00359  -0.1027   0.7720   1.0000
   1.250   0.5946   0.00955   0.00361  -0.1021   0.7591   1.0000
   1.500   0.6208   0.00963   0.00364  -0.1015   0.7461   1.0000
   1.750   0.6470   0.00973   0.00369  -0.1010   0.7329   1.0000
   2.000   0.6733   0.00983   0.00374  -0.1004   0.7195   1.0000
   2.250   0.6994   0.00994   0.00381  -0.0999   0.7058   1.0000
   2.500   0.7256   0.01006   0.00391  -0.0993   0.6918   1.0000
   2.750   0.7516   0.01019   0.00401  -0.0988   0.6776   1.0000
   3.000   0.7776   0.01033   0.00413  -0.0982   0.6631   1.0000
   3.250   0.8035   0.01049   0.00427  -0.0976   0.6484   1.0000
   3.500   0.8293   0.01067   0.00446  -0.0970   0.6336   1.0000
   3.750   0.8550   0.01086   0.00464  -0.0965   0.6186   1.0000
   4.000   0.8803   0.01105   0.00481  -0.0957   0.6016   1.0000
   4.250   0.9036   0.01120   0.00491  -0.0946   0.5747   1.0000
   4.500   0.9263   0.01140   0.00505  -0.0933   0.5443   1.0000
   4.750   0.9485   0.01164   0.00523  -0.0920   0.5104   1.0000
   5.000   0.9699   0.01196   0.00546  -0.0906   0.4704   1.0000
   5.250   0.9858   0.01262   0.00574  -0.0883   0.3844   1.0000
   5.500   0.9817   0.01555   0.00700  -0.0838   0.1164   1.0000
   5.750   0.9925   0.01747   0.00848  -0.0812   0.0461   1.0000
   6.000   1.0087   0.01872   0.00985  -0.0792   0.0383   1.0000
   6.250   1.0268   0.01968   0.01096  -0.0775   0.0356   1.0000
   6.500   1.0422   0.02085   0.01223  -0.0754   0.0334   1.0000
   6.750   1.0564   0.02215   0.01357  -0.0733   0.0316   1.0000
   7.000   1.0682   0.02390   0.01530  -0.0710   0.0293   1.0000
   7.250   1.0845   0.02614   0.01754  -0.0692   0.0278   1.0000
   7.500   1.1073   0.02773   0.01922  -0.0682   0.0272   1.0000
   7.750   1.1330   0.02972   0.02131  -0.0676   0.0269   1.0000
   8.000   1.1614   0.03238   0.02410  -0.0674   0.0272   1.0000
   8.250   1.1949   0.03646   0.02828  -0.0680   0.0284   1.0000
   8.500   1.2173   0.03854   0.03058  -0.0669   0.0287   1.0000
   8.750   1.2374   0.04119   0.03349  -0.0656   0.0288   1.0000
  14.000   0.8070   0.16197   0.15914  -0.0813   0.0582   1.0000
  14.250   0.8054   0.16619   0.16337  -0.0836   0.0551   1.0000
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