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Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Curtis C-72 (curtisc72-il)
Reynolds number: 100,000
Max Cl/Cd: 56.49 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-curtisc72-il-100000-n5.txt
Download as CSV file: xf-curtisc72-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3791   0.09085   0.08565  -0.0446   1.0000   0.0492
 -11.000  -0.3883   0.08705   0.08193  -0.0454   1.0000   0.0494
 -10.750  -0.4011   0.08349   0.07847  -0.0456   1.0000   0.0494
 -10.500  -0.4190   0.08049   0.07558  -0.0445   1.0000   0.0493
 -10.250  -0.4416   0.07783   0.07304  -0.0428   1.0000   0.0491
 -10.000  -0.4616   0.07400   0.06930  -0.0432   1.0000   0.0488
  -9.750  -0.4610   0.06197   0.05710  -0.0582   0.9922   0.0480
  -9.500  -0.4513   0.05042   0.04500  -0.0713   0.9822   0.0476
  -9.250  -0.4320   0.04358   0.03755  -0.0777   0.9746   0.0481
  -9.000  -0.4095   0.03874   0.03206  -0.0814   0.9673   0.0495
  -8.750  -0.3806   0.03487   0.02752  -0.0846   0.9621   0.0504
  -8.500  -0.3533   0.03210   0.02421  -0.0861   0.9559   0.0509
  -8.250  -0.3225   0.02987   0.02159  -0.0877   0.9506   0.0515
  -8.000  -0.2877   0.02818   0.01970  -0.0898   0.9472   0.0524
  -7.750  -0.2601   0.02711   0.01852  -0.0902   0.9401   0.0539
  -7.500  -0.2262   0.02598   0.01719  -0.0917   0.9353   0.0559
  -7.250  -0.1896   0.02470   0.01568  -0.0936   0.9321   0.0576
  -7.000  -0.1620   0.02367   0.01446  -0.0936   0.9246   0.0587
  -6.750  -0.1284   0.02265   0.01326  -0.0946   0.9196   0.0601
  -6.500  -0.0928   0.02166   0.01223  -0.0961   0.9160   0.0619
  -6.250  -0.0667   0.02104   0.01161  -0.0959   0.9076   0.0639
  -6.000  -0.0333   0.02041   0.01094  -0.0969   0.9025   0.0679
  -5.750  -0.0023   0.01985   0.01030  -0.0973   0.8964   0.0723
  -5.500   0.0264   0.01924   0.00972  -0.0975   0.8890   0.0771
  -5.250   0.0604   0.01866   0.00904  -0.0985   0.8842   0.0852
  -5.000   0.0863   0.01816   0.00860  -0.0982   0.8753   0.0974
  -4.750   0.1182   0.01756   0.00810  -0.0989   0.8694   0.1220
  -4.500   0.1455   0.01709   0.00781  -0.0989   0.8612   0.1633
  -4.250   0.1754   0.01650   0.00752  -0.0993   0.8543   0.2374
  -4.000   0.2021   0.01593   0.00749  -0.0993   0.8463   0.3632
  -3.750   0.2301   0.01566   0.00748  -0.0990   0.8385   0.4617
  -3.500   0.2571   0.01552   0.00740  -0.0984   0.8296   0.5109
  -3.250   0.2868   0.01528   0.00715  -0.0982   0.8204   0.5494
  -3.000   0.3124   0.01508   0.00701  -0.0972   0.8076   0.5885
  -2.750   0.3383   0.01483   0.00685  -0.0962   0.7954   0.6373
  -2.500   0.3648   0.01453   0.00667  -0.0952   0.7850   0.6899
  -2.250   0.3897   0.01425   0.00655  -0.0939   0.7747   0.7472
  -2.000   0.4185   0.01389   0.00647  -0.0931   0.7645   0.8570
  -1.750   0.4627   0.01371   0.00619  -0.0961   0.7549   1.0000
  -1.500   0.4898   0.01378   0.00612  -0.0959   0.7434   1.0000
  -1.250   0.5170   0.01386   0.00607  -0.0957   0.7319   1.0000
  -1.000   0.5450   0.01392   0.00600  -0.0956   0.7210   1.0000
  -0.750   0.5726   0.01399   0.00595  -0.0954   0.7094   1.0000
  -0.500   0.5990   0.01411   0.00598  -0.0950   0.6966   1.0000
  -0.250   0.6257   0.01422   0.00601  -0.0947   0.6840   1.0000
   0.000   0.6525   0.01434   0.00603  -0.0943   0.6712   1.0000
   0.250   0.6793   0.01446   0.00606  -0.0940   0.6580   1.0000
   0.500   0.7059   0.01460   0.00611  -0.0936   0.6444   1.0000
   0.750   0.7318   0.01476   0.00621  -0.0931   0.6297   1.0000
   1.000   0.7575   0.01493   0.00632  -0.0927   0.6145   1.0000
   1.250   0.7831   0.01512   0.00645  -0.0922   0.5987   1.0000
   1.500   0.8085   0.01533   0.00659  -0.0916   0.5827   1.0000
   1.750   0.8337   0.01555   0.00675  -0.0911   0.5663   1.0000
   2.000   0.8587   0.01579   0.00694  -0.0905   0.5495   1.0000
   2.250   0.8833   0.01606   0.00715  -0.0900   0.5323   1.0000
   2.500   0.9077   0.01635   0.00739  -0.0894   0.5151   1.0000
   2.750   0.9319   0.01667   0.00766  -0.0887   0.4982   1.0000
   3.000   0.9558   0.01701   0.00795  -0.0881   0.4815   1.0000
   3.250   0.9796   0.01737   0.00827  -0.0875   0.4656   1.0000
   3.500   1.0031   0.01776   0.00862  -0.0868   0.4500   1.0000
   3.750   1.0264   0.01817   0.00898  -0.0862   0.4352   1.0000
   4.000   1.0494   0.01859   0.00936  -0.0855   0.4208   1.0000
   4.250   1.0716   0.01904   0.00978  -0.0847   0.4056   1.0000
   4.500   1.0934   0.01950   0.01020  -0.0838   0.3902   1.0000
   4.750   1.1149   0.01998   0.01065  -0.0830   0.3757   1.0000
   5.000   1.1365   0.02046   0.01115  -0.0822   0.3622   1.0000
   5.250   1.1581   0.02096   0.01170  -0.0814   0.3502   1.0000
   5.500   1.1794   0.02148   0.01224  -0.0806   0.3391   1.0000
   5.750   1.2001   0.02202   0.01280  -0.0797   0.3282   1.0000
   6.000   1.2209   0.02255   0.01344  -0.0788   0.3170   1.0000
   6.250   1.2408   0.02311   0.01407  -0.0779   0.3060   1.0000
   6.500   1.2595   0.02371   0.01470  -0.0767   0.2945   1.0000
   6.750   1.2774   0.02431   0.01539  -0.0755   0.2818   1.0000
   7.000   1.2946   0.02493   0.01612  -0.0742   0.2688   1.0000
   7.250   1.3107   0.02558   0.01689  -0.0727   0.2557   1.0000
   7.500   1.3251   0.02629   0.01768  -0.0711   0.2417   1.0000
   7.750   1.3366   0.02706   0.01850  -0.0690   0.2270   1.0000
   8.000   1.3462   0.02793   0.01940  -0.0668   0.2110   1.0000
   8.250   1.3538   0.02897   0.02042  -0.0645   0.1944   1.0000
   8.500   1.3592   0.03020   0.02162  -0.0621   0.1779   1.0000
   8.750   1.3634   0.03160   0.02297  -0.0599   0.1625   1.0000
   9.000   1.3676   0.03311   0.02447  -0.0579   0.1486   1.0000
   9.250   1.3719   0.03471   0.02609  -0.0561   0.1361   1.0000
   9.500   1.3761   0.03640   0.02783  -0.0544   0.1252   1.0000
   9.750   1.3791   0.03824   0.02974  -0.0529   0.1161   1.0000
  10.000   1.3797   0.04035   0.03190  -0.0514   0.1079   1.0000
  10.250   1.3824   0.04241   0.03407  -0.0502   0.0993   1.0000
  10.500   1.3812   0.04489   0.03661  -0.0491   0.0921   1.0000
  10.750   1.3800   0.04749   0.03932  -0.0482   0.0844   1.0000
  11.000   1.3775   0.05034   0.04228  -0.0475   0.0773   1.0000
  11.250   1.3715   0.05368   0.04569  -0.0471   0.0709   1.0000
  11.500   1.3675   0.05696   0.04912  -0.0468   0.0641   1.0000
  11.750   1.3583   0.06097   0.05317  -0.0469   0.0595   1.0000
  12.000   1.3518   0.06484   0.05720  -0.0471   0.0545   1.0000
  12.250   1.3412   0.06941   0.06184  -0.0478   0.0512   1.0000
  12.500   1.3318   0.07398   0.06652  -0.0486   0.0481   1.0000
  12.750   1.3220   0.07878   0.07147  -0.0496   0.0455   1.0000
  13.000   1.3104   0.08402   0.07680  -0.0510   0.0435   1.0000
  13.250   1.2984   0.08943   0.08226  -0.0526   0.0420   1.0000
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