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HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HOBIESMO1.DAT (hobiesm-il)
Reynolds number: 500,000
Max Cl/Cd: 109.99 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobiesm-il-500000.txt
Download as CSV file: xf-hobiesm-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3754   0.08563   0.08346  -0.0373   1.0000   0.0235
  -8.500  -0.3780   0.08206   0.07994  -0.0380   1.0000   0.0235
  -8.250  -0.4056   0.07634   0.07432  -0.0379   1.0000   0.0245
  -8.000  -0.4185   0.07396   0.07201  -0.0363   1.0000   0.0245
  -7.750  -0.4268   0.07155   0.06965  -0.0358   0.9996   0.0248
  -7.500  -0.4045   0.02688   0.02361  -0.0901   0.9837   0.0158
  -7.250  -0.3732   0.02394   0.02012  -0.0933   0.9779   0.0169
  -7.000  -0.3435   0.01910   0.01472  -0.0967   0.9734   0.0180
  -6.750  -0.3080   0.01740   0.01279  -0.0991   0.9709   0.0191
  -6.500  -0.2761   0.01600   0.01116  -0.1004   0.9656   0.0201
  -6.250  -0.2432   0.01483   0.00980  -0.1018   0.9603   0.0214
  -6.000  -0.2079   0.01409   0.00888  -0.1034   0.9564   0.0229
  -5.750  -0.1785   0.01310   0.00770  -0.1038   0.9481   0.0238
  -5.500  -0.1470   0.01156   0.00597  -0.1048   0.9422   0.0256
  -5.250  -0.1189   0.01093   0.00525  -0.1049   0.9326   0.0275
  -5.000  -0.0895   0.01048   0.00471  -0.1051   0.9242   0.0300
  -4.750  -0.0610   0.01006   0.00417  -0.1051   0.9153   0.0318
  -4.500  -0.0341   0.00953   0.00352  -0.1047   0.9055   0.0355
  -4.250  -0.0065   0.00915   0.00308  -0.1045   0.8968   0.0435
  -4.000   0.0200   0.00868   0.00279  -0.1043   0.8874   0.0894
  -3.750   0.0472   0.00859   0.00265  -0.1040   0.8783   0.1056
  -3.500   0.0745   0.00848   0.00250  -0.1038   0.8699   0.1172
  -3.250   0.1015   0.00836   0.00236  -0.1035   0.8605   0.1274
  -3.000   0.1286   0.00826   0.00223  -0.1032   0.8519   0.1396
  -2.750   0.1558   0.00816   0.00211  -0.1029   0.8433   0.1540
  -2.500   0.1827   0.00804   0.00201  -0.1027   0.8340   0.1709
  -2.250   0.2099   0.00793   0.00191  -0.1024   0.8255   0.1913
  -2.000   0.2368   0.00779   0.00181  -0.1022   0.8163   0.2158
  -1.750   0.2638   0.00767   0.00174  -0.1019   0.8070   0.2439
  -1.500   0.2909   0.00759   0.00168  -0.1017   0.7982   0.2732
  -1.250   0.3179   0.00750   0.00164  -0.1014   0.7882   0.3029
  -1.000   0.3449   0.00742   0.00161  -0.1011   0.7783   0.3345
  -0.750   0.3718   0.00735   0.00158  -0.1009   0.7685   0.3663
  -0.500   0.3986   0.00727   0.00156  -0.1006   0.7580   0.4005
  -0.250   0.4253   0.00716   0.00155  -0.1003   0.7468   0.4425
   0.000   0.4516   0.00701   0.00156  -0.0999   0.7356   0.5071
   0.250   0.4759   0.00666   0.00161  -0.0992   0.7242   0.6485
   0.500   0.5119   0.00594   0.00160  -0.1006   0.7123   1.0000
   0.750   0.5386   0.00603   0.00160  -0.1002   0.6996   1.0000
   1.000   0.5652   0.00612   0.00162  -0.0998   0.6863   1.0000
   1.250   0.5918   0.00622   0.00164  -0.0995   0.6725   1.0000
   1.500   0.6183   0.00632   0.00169  -0.0991   0.6584   1.0000
   1.750   0.6448   0.00644   0.00174  -0.0987   0.6439   1.0000
   2.000   0.6712   0.00657   0.00180  -0.0983   0.6293   1.0000
   2.250   0.6975   0.00671   0.00188  -0.0980   0.6147   1.0000
   2.500   0.7238   0.00685   0.00198  -0.0976   0.6000   1.0000
   2.750   0.7500   0.00699   0.00208  -0.0972   0.5852   1.0000
   3.000   0.7762   0.00715   0.00220  -0.0968   0.5708   1.0000
   3.250   0.8023   0.00732   0.00233  -0.0964   0.5549   1.0000
   3.500   0.8273   0.00753   0.00247  -0.0958   0.5306   1.0000
   3.750   0.8524   0.00775   0.00262  -0.0952   0.5059   1.0000
   4.000   0.8770   0.00801   0.00278  -0.0946   0.4777   1.0000
   4.250   0.9012   0.00831   0.00297  -0.0939   0.4463   1.0000
   4.500   0.9242   0.00873   0.00322  -0.0930   0.4015   1.0000
   4.750   0.9449   0.00938   0.00355  -0.0919   0.3320   1.0000
   5.000   0.9506   0.01171   0.00464  -0.0888   0.1120   1.0000
   5.250   0.9654   0.01321   0.00573  -0.0867   0.0275   1.0000
   5.500   0.9884   0.01374   0.00632  -0.0858   0.0236   1.0000
   5.750   1.0078   0.01469   0.00737  -0.0843   0.0200   1.0000
   6.000   1.0298   0.01526   0.00801  -0.0833   0.0184   1.0000
   6.250   1.0506   0.01594   0.00876  -0.0821   0.0169   1.0000
   6.500   1.0703   0.01672   0.00959  -0.0807   0.0157   1.0000
   6.750   1.0879   0.01765   0.01057  -0.0790   0.0148   1.0000
   7.000   1.1015   0.01899   0.01198  -0.0768   0.0141   1.0000
   7.250   1.1114   0.02103   0.01411  -0.0740   0.0136   1.0000
   7.500   1.1293   0.02236   0.01551  -0.0724   0.0131   1.0000
   7.750   1.1499   0.02292   0.01616  -0.0712   0.0124   1.0000
   8.000   1.1691   0.02419   0.01751  -0.0699   0.0119   1.0000
   8.250   1.1894   0.02578   0.01920  -0.0687   0.0117   1.0000
   8.500   1.2110   0.02767   0.02121  -0.0678   0.0115   1.0000
   8.750   1.2335   0.03011   0.02383  -0.0669   0.0115   1.0000
   9.000   1.2555   0.03387   0.02788  -0.0659   0.0120   1.0000
   9.250   1.2243   0.03984   0.03497  -0.0597   0.0195   1.0000
   9.500   1.2325   0.03817   0.03352  -0.0563   0.0185   1.0000
   9.750   1.2375   0.04005   0.03563  -0.0535   0.0176   1.0000
  10.000   1.2368   0.04285   0.03865  -0.0505   0.0170   1.0000
  10.250   1.2293   0.04566   0.04166  -0.0469   0.0166   1.0000
  10.500   1.2151   0.04823   0.04439  -0.0428   0.0162   1.0000
  10.750   1.1983   0.05124   0.04757  -0.0394   0.0160   1.0000
  11.000   1.1793   0.05480   0.05131  -0.0369   0.0159   1.0000
  11.250   1.1586   0.05894   0.05562  -0.0351   0.0158   1.0000
  11.500   1.1359   0.06383   0.06069  -0.0343   0.0158   1.0000
  11.750   1.1120   0.06930   0.06633  -0.0344   0.0158   1.0000
  12.000   1.0856   0.07563   0.07284  -0.0354   0.0159   1.0000
  12.250   1.0568   0.08269   0.08008  -0.0376   0.0161   1.0000
  12.500   1.0268   0.09024   0.08780  -0.0408   0.0163   1.0000
  12.750   0.9946   0.09845   0.09617  -0.0452   0.0167   1.0000
  13.000   0.9572   0.10677   0.10465  -0.0506   0.0173   1.0000
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