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HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HOBIESMO1.DAT (hobiesm-il)
Reynolds number: 100,000
Max Cl/Cd: 60.89 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobiesm-il-100000.txt
Download as CSV file: xf-hobiesm-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3593   0.09788   0.09306  -0.0324   1.0000   0.1054
  -8.250  -0.3820   0.09749   0.09286  -0.0349   1.0000   0.1068
  -8.000  -0.3985   0.09605   0.09158  -0.0390   1.0000   0.1072
  -7.750  -0.3623   0.08905   0.08446  -0.0319   1.0000   0.1105
  -7.500  -0.3609   0.08661   0.08208  -0.0305   1.0000   0.1133
  -7.250  -0.3682   0.08463   0.08021  -0.0294   1.0000   0.1161
  -7.000  -0.3847   0.08302   0.07874  -0.0323   1.0000   0.1198
  -6.750  -0.4019   0.08043   0.07624  -0.0393   1.0000   0.1214
  -6.500  -0.3986   0.07730   0.07318  -0.0328   1.0000   0.1226
  -6.250  -0.3977   0.07501   0.07093  -0.0290   1.0000   0.1246
  -6.000  -0.3985   0.07283   0.06878  -0.0275   1.0000   0.1276
  -5.750  -0.3964   0.06811   0.06394  -0.0395   1.0000   0.1357
  -5.500  -0.3709   0.04853   0.04357  -0.0561   1.0000   0.0798
  -5.250  -0.3596   0.04525   0.04033  -0.0559   1.0000   0.0817
  -5.000  -0.3378   0.03945   0.03413  -0.0588   1.0000   0.0767
  -4.750  -0.3093   0.03260   0.02649  -0.0628   1.0000   0.0729
  -4.500  -0.2804   0.02825   0.02135  -0.0648   1.0000   0.0731
  -4.250  -0.2544   0.02598   0.01847  -0.0652   1.0000   0.0774
  -4.000  -0.2300   0.02417   0.01626  -0.0653   1.0000   0.0828
  -3.750  -0.2002   0.02284   0.01463  -0.0660   0.9982   0.0898
  -3.500  -0.1573   0.02159   0.01302  -0.0690   0.9924   0.1074
  -3.250  -0.1161   0.02076   0.01231  -0.0721   0.9856   0.1437
  -3.000  -0.0762   0.02068   0.01221  -0.0750   0.9777   0.1840
  -2.750  -0.0331   0.02063   0.01212  -0.0784   0.9705   0.2167
  -2.500   0.0038   0.02030   0.01176  -0.0805   0.9615   0.2393
  -2.250   0.0467   0.01999   0.01134  -0.0836   0.9544   0.2644
  -2.000   0.0842   0.01961   0.01102  -0.0857   0.9454   0.2885
  -1.750   0.1224   0.01929   0.01074  -0.0878   0.9367   0.3222
  -1.500   0.1655   0.01882   0.01045  -0.0908   0.9295   0.3673
  -1.250   0.1995   0.01844   0.01025  -0.0921   0.9196   0.4216
  -1.000   0.2462   0.01778   0.00995  -0.0955   0.9141   0.5072
  -0.750   0.2767   0.01702   0.00987  -0.0956   0.9041   0.6567
  -0.500   0.3387   0.01612   0.00930  -0.1015   0.9002   1.0000
  -0.250   0.3733   0.01619   0.00918  -0.1027   0.8891   1.0000
   0.000   0.4103   0.01620   0.00904  -0.1042   0.8792   1.0000
   0.250   0.4527   0.01606   0.00877  -0.1064   0.8717   1.0000
   0.500   0.4832   0.01612   0.00875  -0.1066   0.8597   1.0000
   0.750   0.5143   0.01616   0.00873  -0.1068   0.8482   1.0000
   1.000   0.5463   0.01616   0.00867  -0.1071   0.8374   1.0000
   1.250   0.5809   0.01603   0.00849  -0.1076   0.8281   1.0000
   1.500   0.6079   0.01612   0.00855  -0.1070   0.8152   1.0000
   1.750   0.6349   0.01621   0.00863  -0.1064   0.8023   1.0000
   2.000   0.6619   0.01629   0.00870  -0.1057   0.7894   1.0000
   2.250   0.6888   0.01637   0.00878  -0.1050   0.7766   1.0000
   2.500   0.7158   0.01645   0.00886  -0.1043   0.7637   1.0000
   2.750   0.7426   0.01652   0.00897  -0.1035   0.7506   1.0000
   3.000   0.7694   0.01660   0.00907  -0.1028   0.7374   1.0000
   3.250   0.7960   0.01669   0.00918  -0.1020   0.7239   1.0000
   3.500   0.8224   0.01679   0.00932  -0.1011   0.7100   1.0000
   3.750   0.8485   0.01690   0.00951  -0.1003   0.6956   1.0000
   4.000   0.8745   0.01704   0.00971  -0.0994   0.6809   1.0000
   4.250   0.9003   0.01720   0.00995  -0.0986   0.6658   1.0000
   4.500   0.9261   0.01737   0.01020  -0.0977   0.6503   1.0000
   4.750   0.9523   0.01722   0.01008  -0.0963   0.6299   1.0000
   5.000   0.9732   0.01683   0.00965  -0.0936   0.5942   1.0000
   5.250   0.9945   0.01663   0.00937  -0.0912   0.5583   1.0000
   5.500   1.0120   0.01662   0.00933  -0.0885   0.5105   1.0000
   5.750   1.0252   0.01689   0.00940  -0.0849   0.4322   1.0000
   6.000   1.0223   0.01899   0.01006  -0.0798   0.2117   1.0000
   6.250   1.0222   0.02210   0.01199  -0.0761   0.0766   1.0000
   6.500   1.0359   0.02364   0.01357  -0.0737   0.0655   1.0000
   6.750   1.0475   0.02521   0.01524  -0.0712   0.0593   1.0000
   7.000   1.0594   0.02666   0.01678  -0.0688   0.0543   1.0000
   7.250   1.0690   0.02846   0.01858  -0.0661   0.0517   1.0000
   7.500   1.0864   0.03083   0.02083  -0.0644   0.0500   1.0000
   7.750   1.1147   0.03282   0.02290  -0.0638   0.0490   1.0000
   8.000   1.1431   0.03485   0.02509  -0.0634   0.0473   1.0000
   8.250   1.1703   0.03711   0.02753  -0.0628   0.0452   1.0000
   8.500   1.1992   0.04008   0.03077  -0.0623   0.0457   1.0000
   8.750   1.2238   0.04349   0.03451  -0.0614   0.0471   1.0000
   9.000   1.2459   0.04788   0.03921  -0.0605   0.0490   1.0000
   9.250   1.2670   0.05030   0.04208  -0.0585   0.0526   1.0000
   9.500   1.2723   0.05514   0.04774  -0.0551   0.0593   1.0000
   9.750   1.2792   0.06068   0.05402  -0.0519   0.0715   1.0000
  10.000   1.2589   0.07418   0.06898  -0.0476   0.1239   1.0000
  10.250   1.2212   0.07679   0.07197  -0.0436   0.1221   1.0000
  10.500   1.1888   0.08021   0.07558  -0.0408   0.1210   1.0000
  10.750   1.1574   0.08510   0.08060  -0.0404   0.1213   1.0000
  11.000   1.1287   0.09112   0.08673  -0.0418   0.1223   1.0000
  11.250   1.0991   0.09829   0.09396  -0.0450   0.1231   1.0000
  11.500   1.0684   0.10684   0.10256  -0.0500   0.1236   1.0000
  11.750   1.0327   0.11799   0.11369  -0.0580   0.1237   1.0000
  12.000   0.9875   0.13177   0.12735  -0.0697   0.1206   1.0000
  12.250   0.9278   0.11123   0.10721  -0.0464   0.0770   1.0000
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