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Curtis C-72 (curtisc72-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Curtis C-72 (curtisc72-il)
Reynolds number: 100,000
Max Cl/Cd: 54.71 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-curtisc72-il-100000.txt
Download as CSV file: xf-curtisc72-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3405   0.09651   0.09153  -0.0350   1.0000   0.1319
 -10.250  -0.3542   0.09472   0.08985  -0.0348   1.0000   0.1362
 -10.000  -0.3978   0.09473   0.09007  -0.0333   1.0000   0.1382
  -9.750  -0.4461   0.09377   0.08929  -0.0360   1.0000   0.1390
  -9.500  -0.4201   0.08970   0.08522  -0.0288   1.0000   0.1410
  -9.250  -0.4112   0.08767   0.08321  -0.0248   1.0000   0.1438
  -9.000  -0.4193   0.08602   0.08163  -0.0225   1.0000   0.1470
  -8.750  -0.4381   0.08410   0.07980  -0.0226   1.0000   0.1514
  -8.500  -0.4652   0.07973   0.07547  -0.0293   1.0000   0.1560
  -8.250  -0.4565   0.07849   0.07430  -0.0227   1.0000   0.1586
  -8.000  -0.4555   0.07672   0.07256  -0.0207   1.0000   0.1638
  -7.750  -0.4629   0.07206   0.06786  -0.0269   1.0000   0.1729
  -7.500  -0.4571   0.07068   0.06652  -0.0229   1.0000   0.1766
  -7.250  -0.4271   0.06577   0.06150  -0.0312   0.9944   0.1907
  -7.000  -0.3684   0.04243   0.03634  -0.0596   0.9892   0.1113
  -6.750  -0.3266   0.03781   0.03115  -0.0642   0.9848   0.1031
  -6.500  -0.2848   0.03358   0.02613  -0.0683   0.9804   0.0984
  -6.250  -0.2431   0.03089   0.02264  -0.0713   0.9750   0.0958
  -6.000  -0.1986   0.02901   0.02039  -0.0748   0.9708   0.0965
  -5.750  -0.1642   0.02783   0.01911  -0.0765   0.9635   0.0997
  -5.500  -0.1210   0.02676   0.01783  -0.0795   0.9583   0.1040
  -5.250  -0.0848   0.02583   0.01665  -0.0810   0.9512   0.1072
  -5.000  -0.0441   0.02469   0.01551  -0.0835   0.9454   0.1124
  -4.750  -0.0052   0.02405   0.01484  -0.0855   0.9389   0.1226
  -4.500   0.0314   0.02324   0.01417  -0.0873   0.9315   0.1397
  -4.250   0.0777   0.02195   0.01333  -0.0909   0.9273   0.1992
  -4.000   0.1073   0.02076   0.01328  -0.0919   0.9184   0.4057
  -3.750   0.1475   0.02053   0.01344  -0.0936   0.9122   0.5557
  -3.500   0.1729   0.02045   0.01358  -0.0926   0.9014   0.6316
  -3.250   0.2187   0.01993   0.01318  -0.0947   0.8955   0.7010
  -3.000   0.2450   0.01958   0.01299  -0.0935   0.8833   0.7580
  -2.750   0.2767   0.01898   0.01269  -0.0924   0.8748   0.8599
  -2.500   0.3331   0.01853   0.01213  -0.0975   0.8669   1.0000
  -2.250   0.3687   0.01850   0.01189  -0.0990   0.8574   1.0000
  -2.000   0.4081   0.01830   0.01150  -0.1008   0.8495   1.0000
  -1.750   0.4375   0.01833   0.01140  -0.1009   0.8386   1.0000
  -1.500   0.4773   0.01801   0.01094  -0.1024   0.8319   1.0000
  -1.250   0.5035   0.01807   0.01090  -0.1019   0.8196   1.0000
  -1.000   0.5341   0.01798   0.01072  -0.1019   0.8094   1.0000
  -0.750   0.5685   0.01770   0.01035  -0.1023   0.8006   1.0000
  -0.500   0.5950   0.01771   0.01029  -0.1016   0.7880   1.0000
  -0.250   0.6238   0.01763   0.01015  -0.1013   0.7764   1.0000
   0.000   0.6585   0.01728   0.00971  -0.1016   0.7673   1.0000
   0.250   0.6847   0.01727   0.00965  -0.1008   0.7532   1.0000
   0.500   0.7116   0.01725   0.00958  -0.1001   0.7392   1.0000
   0.750   0.7391   0.01722   0.00950  -0.0995   0.7248   1.0000
   1.000   0.7667   0.01718   0.00941  -0.0989   0.7098   1.0000
   1.250   0.7942   0.01717   0.00934  -0.0982   0.6940   1.0000
   1.500   0.8214   0.01719   0.00930  -0.0976   0.6775   1.0000
   1.750   0.8483   0.01725   0.00929  -0.0970   0.6603   1.0000
   2.000   0.8753   0.01733   0.00931  -0.0964   0.6426   1.0000
   2.250   0.9022   0.01746   0.00934  -0.0958   0.6247   1.0000
   2.500   0.9274   0.01770   0.00952  -0.0951   0.6059   1.0000
   2.750   0.9519   0.01798   0.00977  -0.0943   0.5868   1.0000
   3.000   0.9768   0.01829   0.01002  -0.0936   0.5688   1.0000
   3.250   1.0017   0.01862   0.01029  -0.0929   0.5514   1.0000
   3.500   1.0266   0.01898   0.01062  -0.0923   0.5349   1.0000
   3.750   1.0511   0.01936   0.01096  -0.0917   0.5188   1.0000
   4.000   1.0752   0.01974   0.01130  -0.0910   0.5028   1.0000
   4.250   1.0988   0.02011   0.01163  -0.0902   0.4865   1.0000
   4.500   1.1222   0.02051   0.01201  -0.0894   0.4707   1.0000
   4.750   1.1453   0.02095   0.01244  -0.0887   0.4557   1.0000
   5.000   1.1684   0.02143   0.01293  -0.0880   0.4416   1.0000
   5.250   1.1916   0.02194   0.01346  -0.0873   0.4279   1.0000
   5.500   1.2147   0.02247   0.01398  -0.0866   0.4143   1.0000
   5.750   1.2379   0.02302   0.01451  -0.0859   0.4008   1.0000
   6.000   1.2605   0.02358   0.01507  -0.0852   0.3866   1.0000
   6.250   1.2810   0.02417   0.01572  -0.0841   0.3715   1.0000
   6.500   1.3010   0.02479   0.01637  -0.0830   0.3559   1.0000
   6.750   1.3205   0.02545   0.01705  -0.0819   0.3398   1.0000
   7.000   1.3381   0.02616   0.01779  -0.0804   0.3227   1.0000
   7.250   1.3526   0.02688   0.01862  -0.0785   0.3042   1.0000
   7.500   1.3649   0.02754   0.01934  -0.0763   0.2847   1.0000
   7.750   1.3751   0.02813   0.01994  -0.0738   0.2653   1.0000
   8.000   1.3834   0.02875   0.02052  -0.0712   0.2470   1.0000
   8.250   1.3891   0.02953   0.02134  -0.0682   0.2292   1.0000
   8.500   1.3931   0.03041   0.02228  -0.0651   0.2130   1.0000
   8.750   1.3964   0.03145   0.02333  -0.0620   0.1981   1.0000
   9.000   1.3992   0.03268   0.02456  -0.0592   0.1840   1.0000
   9.250   1.4012   0.03411   0.02597  -0.0566   0.1705   1.0000
   9.500   1.4017   0.03575   0.02760  -0.0540   0.1573   1.0000
   9.750   1.4006   0.03765   0.02947  -0.0516   0.1441   1.0000
  10.000   1.3974   0.03984   0.03165  -0.0493   0.1308   1.0000
  10.250   1.3926   0.04233   0.03411  -0.0471   0.1177   1.0000
  10.500   1.3881   0.04503   0.03674  -0.0452   0.1054   1.0000
  10.750   1.3833   0.04784   0.03967  -0.0435   0.0952   1.0000
  11.000   1.3814   0.05067   0.04256  -0.0420   0.0867   1.0000
  11.250   1.3843   0.05319   0.04495  -0.0407   0.0798   1.0000
  11.500   1.3840   0.05601   0.04800  -0.0396   0.0747   1.0000
  11.750   1.3964   0.05807   0.04983  -0.0385   0.0695   1.0000
  12.000   1.3927   0.06123   0.05335  -0.0376   0.0667   1.0000
  12.250   1.3921   0.06418   0.05649  -0.0369   0.0637   1.0000
  12.500   1.3985   0.06651   0.05878  -0.0363   0.0607   1.0000
  12.750   1.4047   0.06952   0.06189  -0.0354   0.0586   1.0000
  13.000   1.3983   0.07342   0.06610  -0.0350   0.0574   1.0000
  13.250   1.3902   0.07759   0.07055  -0.0349   0.0563   1.0000
  13.500   1.3802   0.08202   0.07523  -0.0352   0.0554   1.0000
  13.750   1.3688   0.08671   0.08016  -0.0358   0.0546   1.0000
  14.000   1.3552   0.09182   0.08549  -0.0369   0.0539   1.0000
  14.250   1.3388   0.09753   0.09144  -0.0387   0.0534   1.0000
  14.500   1.3185   0.10414   0.09829  -0.0412   0.0532   1.0000
  14.750   1.2810   0.11429   0.10880  -0.0464   0.0541   1.0000
  15.000   1.2288   0.12863   0.12351  -0.0550   0.0560   1.0000
  15.250   1.1803   0.14412   0.13922  -0.0646   0.0578   1.0000
  15.500   1.1389   0.15983   0.15500  -0.0740   0.0592   1.0000
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