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RAF 32 MOD AIRFOIL (raf32md-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RAF 32 MOD AIRFOIL (raf32md-il)
Reynolds number: 50,000
Max Cl/Cd: 38.01 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-raf32md-il-50000.txt
Download as CSV file: xf-raf32md-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAF 32 MOD AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3854   0.10572   0.09918  -0.0262   1.0000   0.2593
  -7.750  -0.3628   0.10056   0.09397  -0.0245   1.0000   0.2690
  -7.500  -0.3989   0.10177   0.09541  -0.0215   1.0000   0.2743
  -7.250  -0.3786   0.09710   0.09070  -0.0198   1.0000   0.2855
  -7.000  -0.4171   0.09819   0.09201  -0.0158   1.0000   0.2893
  -6.750  -0.4049   0.09447   0.08830  -0.0136   1.0000   0.3025
  -6.500  -0.4056   0.09189   0.08578  -0.0108   1.0000   0.3126
  -6.250  -0.4383   0.09215   0.08622  -0.0078   1.0000   0.3196
  -6.000  -0.4319   0.08904   0.08314  -0.0049   1.0000   0.3325
  -5.750  -0.4345   0.08656   0.08073  -0.0023   1.0000   0.3430
  -5.500  -0.4462   0.08468   0.07894  -0.0003   1.0000   0.3546
  -5.250  -0.4571   0.08288   0.07723   0.0013   1.0000   0.3679
  -4.500  -0.3929   0.04969   0.04235  -0.0516   1.0000   0.1570
  -4.250  -0.3693   0.04568   0.03800  -0.0533   1.0000   0.1518
  -4.000  -0.3430   0.04187   0.03366  -0.0556   1.0000   0.1513
  -3.750  -0.3161   0.03862   0.02982  -0.0572   1.0000   0.1512
  -3.500  -0.2894   0.03592   0.02655  -0.0581   1.0000   0.1511
  -3.250  -0.2633   0.03380   0.02389  -0.0585   1.0000   0.1532
  -3.000  -0.2399   0.03230   0.02210  -0.0584   1.0000   0.1599
  -2.750  -0.2164   0.03116   0.02065  -0.0580   1.0000   0.1690
  -2.500  -0.1932   0.03003   0.01944  -0.0576   1.0000   0.1783
  -2.250  -0.1704   0.02909   0.01840  -0.0569   1.0000   0.1928
  -2.000  -0.1483   0.02835   0.01773  -0.0562   1.0000   0.2230
  -1.750  -0.1227   0.02750   0.01724  -0.0558   1.0000   0.3101
  -1.500  -0.1003   0.02660   0.01712  -0.0548   1.0000   0.4606
  -1.250  -0.0873   0.02653   0.01768  -0.0516   1.0000   0.5956
  -1.000  -0.0757   0.02603   0.01774  -0.0475   1.0000   0.7250
  -0.750  -0.0531   0.02491   0.01694  -0.0476   1.0000   1.0000
  -0.500  -0.0258   0.02552   0.01695  -0.0495   1.0000   1.0000
  -0.250  -0.0032   0.02615   0.01718  -0.0500   1.0000   1.0000
   0.000   0.0179   0.02682   0.01753  -0.0503   1.0000   1.0000
   0.250   0.0382   0.02752   0.01795  -0.0504   1.0000   1.0000
   0.500   0.0581   0.02826   0.01845  -0.0504   1.0000   1.0000
   0.750   0.0775   0.02904   0.01903  -0.0504   1.0000   1.0000
   1.000   0.0983   0.02990   0.01970  -0.0507   0.9991   1.0000
   1.250   0.1419   0.03149   0.02107  -0.0553   0.9873   1.0000
   1.500   0.1798   0.03287   0.02229  -0.0588   0.9763   1.0000
   1.750   0.2161   0.03420   0.02347  -0.0618   0.9652   1.0000
   2.000   0.2528   0.03556   0.02473  -0.0649   0.9544   1.0000
   2.250   0.2885   0.03686   0.02594  -0.0677   0.9434   1.0000
   2.500   0.3150   0.03790   0.02693  -0.0690   0.9323   1.0000
   2.750   0.3442   0.03907   0.02806  -0.0706   0.9212   1.0000
   3.000   0.3763   0.04033   0.02929  -0.0727   0.9102   1.0000
   3.250   0.4132   0.04168   0.03065  -0.0754   0.8990   1.0000
   3.500   0.4342   0.04270   0.03168  -0.0757   0.8873   1.0000
   3.750   0.4588   0.04387   0.03287  -0.0765   0.8756   1.0000
   4.000   0.4863   0.04508   0.03413  -0.0776   0.8634   1.0000
   4.250   0.5160   0.04635   0.03546  -0.0791   0.8515   1.0000
   4.500   0.5487   0.04760   0.03679  -0.0808   0.8391   1.0000
   4.750   0.5792   0.04880   0.03808  -0.0822   0.8261   1.0000
   5.000   0.6012   0.04998   0.03939  -0.0824   0.8125   1.0000
   5.250   0.6270   0.05116   0.04068  -0.0830   0.7982   1.0000
   5.500   0.6551   0.05228   0.04193  -0.0837   0.7832   1.0000
   5.750   0.6881   0.05324   0.04305  -0.0848   0.7673   1.0000
   6.000   0.7133   0.05418   0.04418  -0.0847   0.7497   1.0000
   6.250   0.7365   0.05502   0.04519  -0.0843   0.7300   1.0000
   6.500   0.7809   0.05496   0.04539  -0.0853   0.7098   1.0000
   6.750   0.8108   0.05529   0.04598  -0.0849   0.6893   1.0000
   7.000   0.8455   0.05519   0.04617  -0.0845   0.6679   1.0000
   7.250   0.8916   0.05390   0.04524  -0.0841   0.6448   1.0000
   7.500   1.0891   0.03392   0.02654  -0.0832   0.5819   1.0000
   7.750   1.1218   0.02951   0.02222  -0.0765   0.5004   1.0000
   8.000   1.1082   0.02960   0.02140  -0.0670   0.3693   1.0000
   8.250   1.0915   0.03241   0.02295  -0.0601   0.2717   1.0000
   8.500   1.0944   0.03533   0.02511  -0.0566   0.2151   1.0000
   8.750   1.1228   0.03812   0.02744  -0.0562   0.1715   1.0000
   9.000   1.1833   0.04183   0.03077  -0.0602   0.1370   1.0000
   9.250   1.2250   0.04533   0.03442  -0.0617   0.1223   1.0000
   9.500   1.2529   0.04845   0.03773  -0.0616   0.1126   1.0000
   9.750   1.2721   0.05213   0.04185  -0.0603   0.1076   1.0000
  10.000   1.2848   0.05585   0.04611  -0.0581   0.1054   1.0000
  10.250   1.2918   0.05949   0.05019  -0.0557   0.1032   1.0000
  10.500   1.2998   0.06309   0.05405  -0.0536   0.1004   1.0000
  10.750   1.3165   0.06825   0.05921  -0.0534   0.0974   1.0000
  11.000   1.3118   0.07236   0.06372  -0.0503   0.0974   1.0000
  11.250   1.2970   0.07565   0.06750  -0.0463   0.0982   1.0000
  11.500   1.2553   0.07819   0.07052  -0.0402   0.0999   1.0000
  11.750   1.2179   0.08219   0.07487  -0.0365   0.1016   1.0000
  12.000   1.1825   0.08720   0.08015  -0.0349   0.1035   1.0000
  12.250   1.1481   0.09314   0.08630  -0.0350   0.1057   1.0000
  12.500   1.1192   0.09972   0.09301  -0.0365   0.1076   1.0000
  12.750   1.0976   0.10665   0.10003  -0.0386   0.1092   1.0000
  13.000   1.0847   0.11357   0.10700  -0.0407   0.1103   1.0000
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