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HOBIESMO1.DAT (hobiesm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HOBIESMO1.DAT (hobiesm-il)
Reynolds number: 50,000
Max Cl/Cd: 41.71 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hobiesm-il-50000.txt
Download as CSV file: xf-hobiesm-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3858   0.11945   0.11247  -0.0263   1.0000   0.1776
  -9.250  -0.3600   0.11255   0.10552  -0.0244   1.0000   0.1877
  -9.000  -0.3748   0.11270   0.10582  -0.0264   1.0000   0.1916
  -8.750  -0.3525   0.10657   0.09965  -0.0249   1.0000   0.1992
  -8.500  -0.3637   0.10595   0.09917  -0.0260   1.0000   0.2054
  -8.250  -0.3505   0.10118   0.09443  -0.0252   1.0000   0.2107
  -8.000  -0.3526   0.09926   0.09259  -0.0250   1.0000   0.2182
  -7.750  -0.3579   0.09692   0.09039  -0.0248   1.0000   0.2226
  -7.500  -0.3507   0.09379   0.08730  -0.0236   1.0000   0.2312
  -7.250  -0.3795   0.09461   0.08838  -0.0238   1.0000   0.2349
  -7.000  -0.3573   0.08925   0.08298  -0.0209   1.0000   0.2450
  -6.750  -0.3808   0.08918   0.08314  -0.0222   1.0000   0.2497
  -6.500  -0.3716   0.08564   0.07964  -0.0191   1.0000   0.2623
  -6.250  -0.3675   0.08255   0.07657  -0.0166   1.0000   0.2730
  -6.000  -0.3755   0.08058   0.07473  -0.0154   1.0000   0.2817
  -5.500  -0.3818   0.07621   0.07051  -0.0119   1.0000   0.3031
  -5.250  -0.3846   0.07378   0.06815  -0.0106   1.0000   0.3122
  -5.000  -0.3873   0.07151   0.06594  -0.0101   1.0000   0.3247
  -4.750  -0.3421   0.05793   0.05167  -0.0435   1.0000   0.1919
  -4.500  -0.3051   0.04696   0.04003  -0.0542   1.0000   0.1476
  -4.250  -0.2798   0.04214   0.03479  -0.0573   1.0000   0.1457
  -4.000  -0.2533   0.03825   0.03042  -0.0598   1.0000   0.1525
  -3.750  -0.2253   0.03485   0.02649  -0.0617   1.0000   0.1601
  -3.500  -0.1982   0.03216   0.02336  -0.0627   1.0000   0.1730
  -3.250  -0.1746   0.03060   0.02160  -0.0627   1.0000   0.1978
  -3.000  -0.1521   0.02950   0.02035  -0.0622   1.0000   0.2299
  -2.750  -0.1287   0.02850   0.01903  -0.0621   1.0000   0.2636
  -2.500  -0.1079   0.02778   0.01827  -0.0613   1.0000   0.2907
  -2.250  -0.0863   0.02706   0.01745  -0.0609   1.0000   0.3136
  -2.000  -0.0643   0.02651   0.01671  -0.0606   1.0000   0.3381
  -1.750  -0.0429   0.02600   0.01610  -0.0602   1.0000   0.3599
  -1.500  -0.0219   0.02562   0.01564  -0.0597   1.0000   0.3868
  -1.250   0.0012   0.02531   0.01522  -0.0597   1.0000   0.4168
  -1.000   0.0238   0.02506   0.01498  -0.0595   1.0000   0.4571
  -0.750   0.0469   0.02480   0.01481  -0.0595   1.0000   0.5103
  -0.500   0.0697   0.02436   0.01474  -0.0592   1.0000   0.5947
  -0.250   0.0824   0.02287   0.01440  -0.0569   1.0000   1.0000
   0.000   0.1215   0.02387   0.01465  -0.0611   0.9948   1.0000
   0.250   0.1711   0.02507   0.01540  -0.0666   0.9811   1.0000
   0.500   0.2165   0.02615   0.01617  -0.0713   0.9671   1.0000
   0.750   0.2597   0.02716   0.01696  -0.0753   0.9529   1.0000
   1.000   0.3010   0.02811   0.01775  -0.0789   0.9386   1.0000
   1.250   0.3407   0.02903   0.01853  -0.0821   0.9244   1.0000
   1.500   0.3789   0.02990   0.01932  -0.0849   0.9100   1.0000
   1.750   0.4157   0.03076   0.02011  -0.0874   0.8954   1.0000
   2.000   0.4513   0.03159   0.02093  -0.0895   0.8809   1.0000
   2.250   0.4859   0.03241   0.02173  -0.0914   0.8663   1.0000
   2.500   0.5196   0.03321   0.02255  -0.0930   0.8517   1.0000
   2.750   0.5526   0.03400   0.02341  -0.0944   0.8370   1.0000
   3.000   0.5848   0.03478   0.02425  -0.0955   0.8222   1.0000
   3.250   0.6165   0.03554   0.02509  -0.0965   0.8074   1.0000
   3.500   0.6479   0.03628   0.02593  -0.0973   0.7924   1.0000
   3.750   0.6791   0.03700   0.02679  -0.0980   0.7775   1.0000
   4.000   0.7109   0.03765   0.02759  -0.0986   0.7624   1.0000
   4.250   0.7434   0.03823   0.02833  -0.0991   0.7473   1.0000
   4.500   0.7773   0.03870   0.02903  -0.0996   0.7322   1.0000
   4.750   0.8116   0.03904   0.02959  -0.0999   0.7170   1.0000
   5.000   0.8454   0.03928   0.03007  -0.0998   0.7019   1.0000
   5.250   0.8802   0.03937   0.03042  -0.0996   0.6868   1.0000
   5.500   0.9155   0.03932   0.03071  -0.0992   0.6717   1.0000
   5.750   0.9267   0.04082   0.03241  -0.0973   0.6530   1.0000
   6.000   0.9529   0.04131   0.03321  -0.0961   0.6361   1.0000
   6.250   1.0543   0.02748   0.01972  -0.0863   0.5536   1.0000
   6.500   1.0610   0.02544   0.01745  -0.0782   0.4685   1.0000
   6.750   1.0555   0.02596   0.01731  -0.0711   0.3278   1.0000
   7.000   1.0431   0.02918   0.01902  -0.0659   0.1677   1.0000
   7.250   1.0428   0.03204   0.02132  -0.0626   0.1293   1.0000
   7.500   1.0461   0.03445   0.02350  -0.0596   0.1125   1.0000
   7.750   1.0547   0.03644   0.02551  -0.0569   0.1027   1.0000
   8.000   1.0738   0.03854   0.02762  -0.0550   0.0961   1.0000
   8.250   1.1138   0.04086   0.02996  -0.0551   0.0884   1.0000
   8.500   1.1584   0.04383   0.03309  -0.0559   0.0824   1.0000
   8.750   1.1963   0.04726   0.03685  -0.0560   0.0809   1.0000
   9.000   1.2231   0.05101   0.04105  -0.0552   0.0812   1.0000
   9.250   1.2419   0.05509   0.04561  -0.0538   0.0824   1.0000
   9.500   1.2542   0.05931   0.05027  -0.0520   0.0836   1.0000
   9.750   1.2608   0.06362   0.05505  -0.0501   0.0843   1.0000
  10.000   1.2638   0.06805   0.05984  -0.0482   0.0851   1.0000
  10.250   1.2644   0.07273   0.06484  -0.0464   0.0858   1.0000
  10.500   1.2686   0.07811   0.07045  -0.0453   0.0867   1.0000
  10.750   1.2211   0.07986   0.07286  -0.0403   0.0889   1.0000
  11.000   1.1817   0.08420   0.07748  -0.0384   0.0911   1.0000
  11.250   1.1477   0.08977   0.08327  -0.0390   0.0931   1.0000
  11.500   1.1171   0.09630   0.08995  -0.0413   0.0948   1.0000
  11.750   1.0924   0.10353   0.09727  -0.0446   0.0966   1.0000
  12.000   1.0886   0.10995   0.10371  -0.0462   0.0986   1.0000
  12.250   0.8951   0.11926   0.11352  -0.0490   0.0981   1.0000
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