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20-32C AIRFOIL (2032c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: 20-32C AIRFOIL (2032c-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.79 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-2032c-il-1000000.txt
Download as CSV file: xf-2032c-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 20-32C AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2050   0.09104   0.08953  -0.0264   0.9274   0.0092
  -7.250  -0.1979   0.08834   0.08674  -0.0277   0.8965   0.0093
  -7.000  -0.1861   0.08530   0.08360  -0.0304   0.8699   0.0093
  -6.250  -0.1456   0.07584   0.07388  -0.0372   0.8040   0.0099
  -6.000  -0.1270   0.07311   0.07106  -0.0406   0.7831   0.0103
  -5.750  -0.1060   0.07008   0.06794  -0.0446   0.7631   0.0108
  -5.500  -0.0828   0.06677   0.06454  -0.0493   0.7436   0.0113
  -5.250  -0.0533   0.06294   0.06061  -0.0557   0.7254   0.0123
  -5.000  -0.0153   0.05859   0.05615  -0.0647   0.7088   0.0126
  -4.750   0.0168   0.05463   0.05208  -0.0707   0.6924   0.0127
  -4.500   0.0507   0.05039   0.04773  -0.0768   0.6762   0.0127
  -4.250   0.0780   0.04604   0.04327  -0.0816   0.6599   0.0133
  -4.000   0.1061   0.04403   0.04116  -0.0844   0.6416   0.0141
  -3.750   0.1530   0.04026   0.03720  -0.0914   0.6247   0.0168
  -3.500   0.1927   0.03636   0.03312  -0.0966   0.6091   0.0169
  -3.250   0.2332   0.03207   0.02862  -0.1016   0.5943   0.0170
  -3.000   0.3053   0.01399   0.00917  -0.1160   0.5879   0.0166
  -2.750   0.3366   0.01245   0.00721  -0.1170   0.5717   0.0181
  -2.500   0.3639   0.01297   0.00774  -0.1168   0.5537   0.0190
  -2.250   0.3927   0.01272   0.00732  -0.1170   0.5362   0.0205
  -2.000   0.4224   0.01219   0.00655  -0.1172   0.5192   0.0220
  -1.750   0.4527   0.01111   0.00515  -0.1178   0.5035   0.0240
  -1.500   0.4811   0.01105   0.00502  -0.1179   0.4877   0.0257
  -1.250   0.5099   0.01082   0.00467  -0.1180   0.4723   0.0271
  -1.000   0.5389   0.01049   0.00418  -0.1181   0.4570   0.0285
  -0.750   0.5675   0.01037   0.00393  -0.1182   0.4416   0.0299
  -0.500   0.5956   0.01056   0.00403  -0.1181   0.4267   0.0309
  -0.250   0.6249   0.00996   0.00327  -0.1183   0.4134   0.0316
   0.000   0.6539   0.00955   0.00274  -0.1185   0.4009   0.0323
   0.250   0.6828   0.00931   0.00242  -0.1187   0.3886   0.0341
   0.500   0.7113   0.00924   0.00227  -0.1188   0.3765   0.0355
   0.750   0.7398   0.00922   0.00217  -0.1189   0.3647   0.0369
   1.000   0.7682   0.00922   0.00211  -0.1189   0.3537   0.0380
   1.250   0.7964   0.00926   0.00208  -0.1189   0.3438   0.0390
   1.750   0.8528   0.00937   0.00207  -0.1190   0.3264   0.0418
   2.000   0.8809   0.00943   0.00210  -0.1190   0.3187   0.0524
   2.250   0.9097   0.00925   0.00226  -0.1193   0.3121   0.2240
   2.500   0.9378   0.00926   0.00242  -0.1195   0.3050   0.3250
   2.750   0.9613   0.00817   0.00262  -0.1189   0.3002   1.0000
   3.000   0.9890   0.00833   0.00271  -0.1189   0.2945   1.0000
   3.250   1.0167   0.00849   0.00282  -0.1188   0.2897   1.0000
   3.500   1.0445   0.00862   0.00292  -0.1188   0.2857   1.0000
   3.750   1.0721   0.00878   0.00305  -0.1188   0.2815   1.0000
   4.000   1.0993   0.00899   0.00321  -0.1187   0.2767   1.0000
   4.250   1.1271   0.00909   0.00331  -0.1187   0.2722   1.0000
   4.500   1.1542   0.00929   0.00344  -0.1186   0.2648   1.0000
   4.750   1.1815   0.00944   0.00359  -0.1186   0.2598   1.0000
   5.000   1.2088   0.00959   0.00373  -0.1185   0.2550   1.0000
   5.250   1.2356   0.00982   0.00390  -0.1185   0.2478   1.0000
   5.500   1.2628   0.00996   0.00405  -0.1184   0.2412   1.0000
   5.750   1.2894   0.01019   0.00423  -0.1183   0.2327   1.0000
   6.000   1.3154   0.01048   0.00442  -0.1182   0.2142   1.0000
   6.250   1.3360   0.01160   0.00505  -0.1174   0.1481   1.0000
   6.500   1.3471   0.01417   0.00692  -0.1154   0.0164   1.0000
   6.750   1.3720   0.01456   0.00738  -0.1150   0.0146   1.0000
   7.000   1.3962   0.01505   0.00793  -0.1145   0.0126   1.0000
   7.250   1.4194   0.01565   0.00862  -0.1139   0.0111   1.0000
   7.500   1.4433   0.01612   0.00914  -0.1133   0.0105   1.0000
   7.750   1.4663   0.01668   0.00976  -0.1127   0.0098   1.0000
   8.000   1.4886   0.01729   0.01044  -0.1120   0.0092   1.0000
   8.250   1.5100   0.01799   0.01119  -0.1111   0.0086   1.0000
   8.500   1.5289   0.01894   0.01223  -0.1100   0.0079   1.0000
   8.750   1.5411   0.02053   0.01400  -0.1079   0.0073   1.0000
   9.000   1.5613   0.02115   0.01468  -0.1069   0.0070   1.0000
   9.250   1.5778   0.02208   0.01569  -0.1055   0.0067   1.0000
   9.500   1.5916   0.02315   0.01686  -0.1037   0.0065   1.0000
   9.750   1.6029   0.02433   0.01812  -0.1016   0.0062   1.0000
  10.000   1.6102   0.02558   0.01946  -0.0990   0.0060   1.0000
  10.250   1.6121   0.02689   0.02087  -0.0956   0.0059   1.0000
  10.500   1.6129   0.02846   0.02253  -0.0927   0.0057   1.0000
  10.750   1.6135   0.03029   0.02447  -0.0903   0.0055   1.0000
  11.000   1.6126   0.03251   0.02678  -0.0885   0.0054   1.0000
  11.250   1.6099   0.03522   0.02959  -0.0873   0.0053   1.0000
  11.500   1.6043   0.03857   0.03304  -0.0866   0.0052   1.0000
  11.750   1.5959   0.04259   0.03718  -0.0865   0.0051   1.0000
  12.000   1.5852   0.04715   0.04185  -0.0867   0.0050   1.0000
  12.250   1.5713   0.05224   0.04705  -0.0871   0.0049   1.0000
  12.500   1.5545   0.05755   0.05246  -0.0872   0.0048   1.0000
  12.750   1.5367   0.06222   0.05718  -0.0856   0.0047   1.0000
  13.000   1.5334   0.06601   0.06108  -0.0860   0.0047   1.0000
  13.250   1.5314   0.06990   0.06508  -0.0870   0.0046   1.0000
  13.500   1.5292   0.07382   0.06910  -0.0878   0.0045   1.0000
  13.750   1.5260   0.07758   0.07295  -0.0881   0.0044   1.0000
  14.000   1.5237   0.08098   0.07642  -0.0878   0.0043   1.0000
  14.250   1.5230   0.08414   0.07965  -0.0874   0.0043   1.0000
  14.500   1.5235   0.08696   0.08254  -0.0866   0.0042   1.0000
  14.750   1.5245   0.08972   0.08539  -0.0858   0.0042   1.0000
  15.000   1.5256   0.09255   0.08830  -0.0850   0.0041   1.0000
  15.250   1.5261   0.09560   0.09146  -0.0845   0.0041   1.0000
  15.500   1.5262   0.09872   0.09468  -0.0839   0.0041   1.0000
  15.750   1.5244   0.10232   0.09840  -0.0840   0.0040   1.0000
  16.000   1.5219   0.10615   0.10235  -0.0842   0.0040   1.0000
  16.250   1.5182   0.11030   0.10663  -0.0848   0.0039   1.0000
  16.500   1.5121   0.11498   0.11145  -0.0857   0.0040   1.0000
  16.750   1.5036   0.12022   0.11685  -0.0873   0.0040   1.0000
  17.000   1.4933   0.12591   0.12268  -0.0892   0.0041   1.0000
  17.250   1.4812   0.13208   0.12901  -0.0916   0.0043   1.0000
  17.750   1.4614   0.14336   0.14052  -0.0922   0.0047   1.0000
  18.000   1.4485   0.15018   0.14748  -0.0969   0.0047   1.0000
  18.250   1.4363   0.15715   0.15457  -0.1018   0.0047   1.0000
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