Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Curtis C-72 (curtisc72-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-curtisc72-il-1000000.txt
Download as CSV file: xf-curtisc72-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Curtis C-72                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.7636   0.04425   0.04196  -0.0847   1.0000   0.0198
 -14.000  -0.8081   0.03816   0.03570  -0.0882   1.0000   0.0198
 -13.750  -0.8177   0.03571   0.03309  -0.0871   0.9994   0.0199
 -13.500  -0.8066   0.02948   0.02635  -0.0939   0.9954   0.0204
 -13.250  -0.7777   0.02805   0.02485  -0.0961   0.9940   0.0207
 -13.000  -0.7485   0.02744   0.02421  -0.0973   0.9915   0.0210
 -12.750  -0.7181   0.02686   0.02361  -0.0986   0.9891   0.0214
 -12.500  -0.6872   0.02609   0.02279  -0.1001   0.9871   0.0218
 -12.250  -0.6571   0.02475   0.02132  -0.1019   0.9852   0.0223
 -12.000  -0.6263   0.02326   0.01964  -0.1039   0.9838   0.0228
 -11.750  -0.5988   0.02202   0.01821  -0.1048   0.9801   0.0233
 -11.500  -0.5698   0.02125   0.01729  -0.1056   0.9760   0.0238
 -11.250  -0.5381   0.02109   0.01702  -0.1064   0.9728   0.0241
 -11.000  -0.5174   0.01801   0.01366  -0.1069   0.9670   0.0249
 -10.750  -0.4910   0.01718   0.01278  -0.1070   0.9609   0.0253
 -10.500  -0.4629   0.01651   0.01204  -0.1072   0.9559   0.0257
 -10.250  -0.4376   0.01590   0.01135  -0.1068   0.9480   0.0261
 -10.000  -0.4103   0.01536   0.01073  -0.1067   0.9419   0.0266
  -9.750  -0.3848   0.01486   0.01016  -0.1062   0.9338   0.0271
  -9.250  -0.3324   0.01372   0.00882  -0.1054   0.9191   0.0280
  -9.000  -0.3057   0.01326   0.00825  -0.1050   0.9121   0.0283
  -8.750  -0.2791   0.01287   0.00779  -0.1047   0.9046   0.0286
  -8.500  -0.2519   0.01261   0.00744  -0.1043   0.8974   0.0289
  -8.250  -0.2274   0.01147   0.00621  -0.1038   0.8901   0.0296
  -8.000  -0.2013   0.01091   0.00560  -0.1034   0.8825   0.0301
  -7.750  -0.1745   0.01050   0.00515  -0.1031   0.8754   0.0306
  -7.500  -0.1476   0.01015   0.00475  -0.1028   0.8676   0.0311
  -7.250  -0.1204   0.00985   0.00440  -0.1025   0.8605   0.0316
  -7.000  -0.0931   0.00955   0.00406  -0.1022   0.8523   0.0322
  -6.750  -0.0657   0.00930   0.00375  -0.1019   0.8442   0.0328
  -6.500  -0.0384   0.00907   0.00346  -0.1016   0.8343   0.0334
  -6.250  -0.0108   0.00888   0.00322  -0.1014   0.8240   0.0340
  -6.000   0.0166   0.00873   0.00300  -0.1011   0.8136   0.0345
  -5.750   0.0439   0.00845   0.00265  -0.1008   0.8023   0.0352
  -5.500   0.0712   0.00821   0.00236  -0.1005   0.7903   0.0364
  -5.250   0.0988   0.00806   0.00215  -0.1003   0.7788   0.0377
  -5.000   0.1265   0.00794   0.00198  -0.1000   0.7685   0.0390
  -4.750   0.1545   0.00783   0.00183  -0.0999   0.7585   0.0406
  -4.500   0.1823   0.00772   0.00168  -0.0997   0.7485   0.0439
  -4.250   0.2100   0.00757   0.00157  -0.0995   0.7382   0.0565
  -4.000   0.2377   0.00737   0.00147  -0.0994   0.7288   0.0895
  -3.750   0.2652   0.00724   0.00139  -0.0993   0.7190   0.1179
  -3.500   0.2927   0.00704   0.00133  -0.0992   0.7086   0.1681
  -3.250   0.3201   0.00683   0.00127  -0.0992   0.6985   0.2283
  -3.000   0.3471   0.00661   0.00124  -0.0990   0.6883   0.3035
  -2.750   0.3747   0.00642   0.00123  -0.0990   0.6786   0.3720
  -2.500   0.4021   0.00633   0.00125  -0.0989   0.6687   0.4276
  -2.250   0.4297   0.00630   0.00127  -0.0988   0.6577   0.4678
  -2.000   0.4576   0.00629   0.00129  -0.0987   0.6465   0.4936
  -1.750   0.4854   0.00632   0.00131  -0.0986   0.6354   0.5124
  -1.250   0.5406   0.00632   0.00138  -0.0984   0.6126   0.5649
  -1.000   0.5680   0.00633   0.00142  -0.0983   0.6005   0.5935
  -0.750   0.5952   0.00634   0.00147  -0.0981   0.5872   0.6221
  -0.250   0.6481   0.00626   0.00160  -0.0976   0.5592   0.7298
   0.000   0.6820   0.00583   0.00170  -0.0986   0.5433   1.0000
   0.250   0.7086   0.00597   0.00176  -0.0984   0.5262   1.0000
   0.500   0.7351   0.00613   0.00184  -0.0981   0.5078   1.0000
   0.750   0.7614   0.00631   0.00192  -0.0979   0.4877   1.0000
   1.000   0.7871   0.00653   0.00203  -0.0975   0.4652   1.0000
   1.250   0.8128   0.00677   0.00214  -0.0972   0.4391   1.0000
   1.500   0.8380   0.00705   0.00228  -0.0968   0.4109   1.0000
   2.000   0.8890   0.00758   0.00258  -0.0962   0.3681   1.0000
   2.250   0.9149   0.00780   0.00273  -0.0959   0.3535   1.0000
   2.500   0.9413   0.00799   0.00287  -0.0958   0.3427   1.0000
   2.750   0.9678   0.00817   0.00302  -0.0957   0.3333   1.0000
   3.000   0.9937   0.00840   0.00319  -0.0955   0.3234   1.0000
   3.250   1.0204   0.00855   0.00334  -0.0954   0.3158   1.0000
   3.500   1.0463   0.00878   0.00352  -0.0952   0.3078   1.0000
   3.750   1.0731   0.00892   0.00367  -0.0952   0.3015   1.0000
   4.000   1.0989   0.00913   0.00386  -0.0950   0.2940   1.0000
   4.250   1.1253   0.00930   0.00403  -0.0949   0.2875   1.0000
   4.500   1.1510   0.00952   0.00423  -0.0948   0.2792   1.0000
   4.750   1.1768   0.00973   0.00441  -0.0946   0.2683   1.0000
   5.000   1.2018   0.00999   0.00463  -0.0944   0.2547   1.0000
   5.250   1.2261   0.01031   0.00486  -0.0940   0.2371   1.0000
   5.500   1.2492   0.01071   0.00515  -0.0935   0.2162   1.0000
   5.750   1.2713   0.01118   0.00549  -0.0929   0.1902   1.0000
   6.000   1.2927   0.01170   0.00589  -0.0921   0.1668   1.0000
   6.250   1.3132   0.01228   0.00634  -0.0912   0.1451   1.0000
   6.500   1.3342   0.01281   0.00677  -0.0904   0.1271   1.0000
   6.750   1.3550   0.01333   0.00722  -0.0896   0.1125   1.0000
   7.000   1.3760   0.01381   0.00765  -0.0888   0.1016   1.0000
   7.250   1.3966   0.01431   0.00809  -0.0880   0.0921   1.0000
   7.500   1.4173   0.01477   0.00853  -0.0871   0.0845   1.0000
   7.750   1.4375   0.01524   0.00898  -0.0863   0.0766   1.0000
   8.000   1.4561   0.01579   0.00949  -0.0852   0.0672   1.0000
   8.250   1.4708   0.01649   0.01010  -0.0834   0.0530   1.0000
   8.500   1.4798   0.01749   0.01096  -0.0808   0.0360   1.0000
   8.750   1.4909   0.01837   0.01179  -0.0785   0.0277   1.0000
   9.000   1.5030   0.01918   0.01261  -0.0765   0.0235   1.0000
   9.250   1.5149   0.02002   0.01346  -0.0746   0.0210   1.0000
   9.500   1.5278   0.02081   0.01429  -0.0729   0.0194   1.0000
   9.750   1.5403   0.02164   0.01516  -0.0713   0.0181   1.0000
  10.000   1.5500   0.02268   0.01624  -0.0694   0.0169   1.0000
  10.250   1.5608   0.02368   0.01730  -0.0678   0.0161   1.0000
  10.500   1.5724   0.02466   0.01834  -0.0664   0.0155   1.0000
  10.750   1.5827   0.02576   0.01950  -0.0650   0.0149   1.0000
  11.000   1.5913   0.02702   0.02081  -0.0635   0.0144   1.0000
  11.250   1.5967   0.02858   0.02243  -0.0619   0.0138   1.0000
  11.500   1.5982   0.03054   0.02448  -0.0601   0.0133   1.0000
  11.750   1.6067   0.03198   0.02600  -0.0591   0.0130   1.0000
  12.000   1.6134   0.03360   0.02771  -0.0581   0.0127   1.0000
  12.250   1.6189   0.03540   0.02958  -0.0572   0.0124   1.0000
  12.500   1.6234   0.03735   0.03161  -0.0563   0.0121   1.0000
  12.750   1.6266   0.03949   0.03382  -0.0556   0.0118   1.0000
  13.000   1.6280   0.04188   0.03629  -0.0549   0.0115   1.0000
  13.250   1.6264   0.04469   0.03918  -0.0544   0.0112   1.0000
  13.500   1.6211   0.04802   0.04262  -0.0540   0.0110   1.0000
  13.750   1.6116   0.05201   0.04672  -0.0538   0.0108   1.0000
  14.000   1.5990   0.05659   0.05143  -0.0540   0.0106   1.0000
  14.250   1.5968   0.05998   0.05491  -0.0543   0.0105   1.0000
  14.500   1.5928   0.06369   0.05873  -0.0548   0.0104   1.0000
  14.750   1.5868   0.06776   0.06291  -0.0554   0.0103   1.0000
  15.000   1.5797   0.07212   0.06738  -0.0563   0.0102   1.0000
  15.250   1.5701   0.07688   0.07225  -0.0574   0.0101   1.0000
  15.500   1.5603   0.08179   0.07727  -0.0586   0.0100   1.0000
  15.750   1.5490   0.08704   0.08263  -0.0600   0.0099   1.0000
  16.000   1.5374   0.09239   0.08809  -0.0615   0.0098   1.0000
  16.250   1.5246   0.09799   0.09380  -0.0633   0.0097   1.0000
  16.500   1.5121   0.10362   0.09954  -0.0651   0.0096   1.0000
<< Back to Curtis C-72 (curtisc72-il)

Polar data table (+)

Polar graphs


<< Back to Curtis C-72 (curtisc72-il)