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Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Curtis C-72 (curtisc72-il)
Reynolds number: 200,000
Max Cl/Cd: 76.3 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-curtisc72-il-200000.txt
Download as CSV file: xf-curtisc72-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3609   0.08884   0.08535  -0.0387   1.0000   0.0745
 -10.250  -0.3749   0.08698   0.08358  -0.0367   1.0000   0.0759
 -10.000  -0.3977   0.08566   0.08235  -0.0335   1.0000   0.0770
  -9.750  -0.4265   0.08471   0.08150  -0.0294   1.0000   0.0775
  -9.500  -0.4457   0.06976   0.06642  -0.0569   0.9913   0.0816
  -9.250  -0.4213   0.06853   0.06529  -0.0541   0.9887   0.0827
  -9.000  -0.3948   0.06742   0.06418  -0.0533   0.9856   0.0849
  -8.750  -0.3683   0.06175   0.05840  -0.0623   0.9793   0.0899
  -8.500  -0.3434   0.05142   0.04765  -0.0773   0.9717   0.0970
  -8.250  -0.3247   0.03606   0.03087  -0.0863   0.9623   0.0671
  -8.000  -0.2916   0.03165   0.02608  -0.0897   0.9588   0.0651
  -7.750  -0.2596   0.02747   0.02130  -0.0919   0.9545   0.0621
  -7.500  -0.2285   0.02465   0.01793  -0.0930   0.9486   0.0609
  -7.250  -0.1903   0.02286   0.01583  -0.0952   0.9453   0.0612
  -7.000  -0.1491   0.02165   0.01447  -0.0979   0.9431   0.0631
  -6.750  -0.1184   0.02059   0.01323  -0.0984   0.9364   0.0643
  -6.500  -0.0808   0.01945   0.01192  -0.1001   0.9323   0.0655
  -6.250  -0.0411   0.01844   0.01079  -0.1021   0.9294   0.0670
  -6.000  -0.0011   0.01752   0.00977  -0.1042   0.9269   0.0688
  -5.750   0.0240   0.01668   0.00900  -0.1036   0.9178   0.0722
  -5.500   0.0601   0.01602   0.00835  -0.1050   0.9137   0.0768
  -5.250   0.0907   0.01544   0.00773  -0.1052   0.9072   0.0814
  -5.000   0.1205   0.01474   0.00711  -0.1054   0.9001   0.0905
  -4.750   0.1540   0.01387   0.00637  -0.1062   0.8956   0.1201
  -4.500   0.1782   0.01310   0.00602  -0.1056   0.8853   0.2042
  -4.250   0.2085   0.01225   0.00569  -0.1059   0.8787   0.3481
  -4.000   0.2329   0.01192   0.00561  -0.1048   0.8668   0.4404
  -3.750   0.2593   0.01170   0.00549  -0.1040   0.8562   0.5010
  -3.500   0.2874   0.01148   0.00534  -0.1034   0.8481   0.5500
  -3.250   0.3122   0.01137   0.00532  -0.1024   0.8378   0.5912
  -3.000   0.3402   0.01117   0.00516  -0.1019   0.8303   0.6284
  -2.750   0.3651   0.01103   0.00510  -0.1009   0.8196   0.6613
  -2.500   0.3910   0.01083   0.00499  -0.1001   0.8106   0.6984
  -2.250   0.4155   0.01053   0.00488  -0.0988   0.8013   0.7544
  -2.000   0.4450   0.01010   0.00483  -0.0980   0.7913   0.9025
  -1.750   0.4915   0.00997   0.00457  -0.1016   0.7824   1.0000
  -1.500   0.5181   0.01003   0.00451  -0.1013   0.7710   1.0000
  -1.250   0.5451   0.01008   0.00446  -0.1010   0.7599   1.0000
  -1.000   0.5727   0.01013   0.00437  -0.1008   0.7492   1.0000
  -0.750   0.5995   0.01020   0.00434  -0.1004   0.7373   1.0000
  -0.500   0.6259   0.01029   0.00435  -0.0999   0.7250   1.0000
  -0.250   0.6526   0.01038   0.00436  -0.0996   0.7127   1.0000
   0.000   0.6793   0.01047   0.00436  -0.0992   0.7001   1.0000
   0.250   0.7060   0.01058   0.00436  -0.0988   0.6869   1.0000
   0.500   0.7320   0.01069   0.00441  -0.0983   0.6727   1.0000
   0.750   0.7579   0.01082   0.00448  -0.0978   0.6578   1.0000
   1.000   0.7836   0.01096   0.00454  -0.0973   0.6419   1.0000
   1.250   0.8092   0.01111   0.00462  -0.0967   0.6252   1.0000
   1.500   0.8346   0.01129   0.00471  -0.0961   0.6079   1.0000
   1.750   0.8593   0.01147   0.00484  -0.0955   0.5884   1.0000
   2.000   0.8838   0.01169   0.00499  -0.0948   0.5679   1.0000
   2.250   0.9082   0.01194   0.00514  -0.0941   0.5473   1.0000
   2.500   0.9322   0.01223   0.00532  -0.0934   0.5264   1.0000
   2.750   0.9560   0.01253   0.00555  -0.0927   0.5052   1.0000
   3.000   0.9796   0.01287   0.00578  -0.0920   0.4854   1.0000
   3.250   1.0029   0.01323   0.00603  -0.0912   0.4663   1.0000
   3.500   1.0260   0.01359   0.00631  -0.0905   0.4471   1.0000
   3.750   1.0492   0.01395   0.00661  -0.0898   0.4302   1.0000
   4.000   1.0729   0.01435   0.00694  -0.0893   0.4165   1.0000
   4.250   1.0966   0.01473   0.00730  -0.0887   0.4037   1.0000
   4.500   1.1205   0.01510   0.00769  -0.0882   0.3919   1.0000
   4.750   1.1442   0.01552   0.00809  -0.0877   0.3809   1.0000
   5.000   1.1674   0.01597   0.00848  -0.0871   0.3700   1.0000
   5.250   1.1903   0.01634   0.00892  -0.0865   0.3584   1.0000
   5.500   1.2131   0.01675   0.00937  -0.0859   0.3473   1.0000
   5.750   1.2355   0.01722   0.00982  -0.0852   0.3369   1.0000
   6.000   1.2572   0.01765   0.01028  -0.0844   0.3255   1.0000
   6.250   1.2782   0.01806   0.01078  -0.0836   0.3131   1.0000
   6.500   1.2979   0.01850   0.01125  -0.0825   0.2993   1.0000
   6.750   1.3155   0.01892   0.01169  -0.0811   0.2820   1.0000
   7.000   1.3312   0.01939   0.01213  -0.0794   0.2625   1.0000
   7.250   1.3471   0.01987   0.01264  -0.0779   0.2409   1.0000
   7.500   1.3612   0.02049   0.01324  -0.0760   0.2198   1.0000
   7.750   1.3722   0.02124   0.01393  -0.0738   0.1995   1.0000
   8.000   1.3826   0.02212   0.01475  -0.0715   0.1801   1.0000
   8.250   1.3916   0.02313   0.01571  -0.0693   0.1637   1.0000
   8.500   1.4004   0.02421   0.01676  -0.0671   0.1498   1.0000
   8.750   1.4090   0.02534   0.01789  -0.0651   0.1373   1.0000
   9.000   1.4170   0.02656   0.01911  -0.0631   0.1256   1.0000
   9.250   1.4238   0.02790   0.02045  -0.0612   0.1140   1.0000
   9.500   1.4289   0.02941   0.02198  -0.0593   0.1017   1.0000
   9.750   1.4317   0.03119   0.02376  -0.0573   0.0875   1.0000
  10.000   1.4304   0.03339   0.02592  -0.0553   0.0733   1.0000
  10.250   1.4278   0.03583   0.02833  -0.0534   0.0622   1.0000
  10.500   1.4256   0.03834   0.03087  -0.0518   0.0550   1.0000
  10.750   1.4203   0.04125   0.03376  -0.0504   0.0506   1.0000
  11.000   1.4199   0.04381   0.03645  -0.0493   0.0471   1.0000
  11.250   1.4173   0.04668   0.03937  -0.0485   0.0445   1.0000
  11.500   1.4092   0.05017   0.04288  -0.0476   0.0427   1.0000
  11.750   1.4079   0.05308   0.04594  -0.0470   0.0409   1.0000
  12.000   1.4063   0.05609   0.04906  -0.0466   0.0392   1.0000
  12.250   1.4036   0.05929   0.05233  -0.0464   0.0377   1.0000
  12.500   1.3995   0.06267   0.05576  -0.0463   0.0365   1.0000
  12.750   1.3958   0.06593   0.05902  -0.0456   0.0353   1.0000
  13.000   1.3958   0.06901   0.06226  -0.0456   0.0345   1.0000
  13.250   1.3957   0.07211   0.06549  -0.0455   0.0335   1.0000
  13.500   1.3958   0.07521   0.06870  -0.0455   0.0327   1.0000
  13.750   1.3960   0.07830   0.07188  -0.0455   0.0319   1.0000
  14.000   1.3967   0.08130   0.07495  -0.0456   0.0311   1.0000
  14.250   1.3995   0.08389   0.07754  -0.0452   0.0303   1.0000
  14.500   1.4029   0.08636   0.08005  -0.0443   0.0294   1.0000
  14.750   1.3982   0.09052   0.08441  -0.0453   0.0290   1.0000
  15.000   1.3928   0.09482   0.08892  -0.0465   0.0285   1.0000
  15.250   1.3872   0.09921   0.09350  -0.0478   0.0281   1.0000
  15.500   1.3811   0.10378   0.09825  -0.0492   0.0277   1.0000
  15.750   1.3744   0.10854   0.10318  -0.0508   0.0274   1.0000
  16.000   1.3665   0.11361   0.10844  -0.0528   0.0271   1.0000
  16.250   1.3569   0.11911   0.11412  -0.0552   0.0269   1.0000
  16.500   1.3456   0.12510   0.12031  -0.0581   0.0267   1.0000
  16.750   1.3318   0.13181   0.12722  -0.0617   0.0266   1.0000
  17.000   1.3143   0.13961   0.13525  -0.0662   0.0267   1.0000
  17.250   1.2914   0.14907   0.14496  -0.0720   0.0268   1.0000
  17.500   1.2585   0.16163   0.15781  -0.0802   0.0273   1.0000
  17.750   1.2040   0.18163   0.17813  -0.0933   0.0283   1.0000
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