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CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: CURTISS CR-1 AIRFOIL (cr1-il)
Reynolds number: 100,000
Max Cl/Cd: 53 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cr1-il-100000-n5.txt
Download as CSV file: xf-cr1-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CURTISS CR-1 AIRFOIL                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3013   0.11752   0.11226  -0.0471   1.0000   0.0558
 -10.750  -0.2996   0.11501   0.10979  -0.0462   1.0000   0.0555
 -10.500  -0.3014   0.11270   0.10754  -0.0451   1.0000   0.0551
 -10.250  -0.3097   0.11042   0.10534  -0.0439   1.0000   0.0551
 -10.000  -0.3177   0.10748   0.10245  -0.0442   0.9988   0.0554
  -9.750  -0.3138   0.10124   0.09620  -0.0507   0.9918   0.0559
  -9.250  -0.2969   0.09122   0.08616  -0.0601   0.9779   0.0560
  -9.000  -0.2894   0.08589   0.08081  -0.0654   0.9706   0.0560
  -8.750  -0.2691   0.08418   0.07911  -0.0668   0.9638   0.0570
  -8.500  -0.2490   0.08189   0.07680  -0.0696   0.9576   0.0587
  -8.250  -0.2414   0.07748   0.07238  -0.0744   0.9488   0.0594
  -8.000  -0.2349   0.07199   0.06687  -0.0813   0.9406   0.0599
  -7.750  -0.2344   0.06602   0.06084  -0.0875   0.9288   0.0600
  -7.500  -0.2341   0.05891   0.05359  -0.0945   0.9184   0.0604
  -7.250  -0.2388   0.04901   0.04335  -0.1021   0.9085   0.0618
  -7.000  -0.2729   0.03564   0.02874  -0.1041   0.8939   0.0644
  -6.750  -0.2563   0.03354   0.02636  -0.1036   0.8876   0.0657
  -6.500  -0.2367   0.03240   0.02508  -0.1029   0.8807   0.0669
  -6.250  -0.2121   0.03083   0.02326  -0.1032   0.8764   0.0687
  -6.000  -0.1954   0.02942   0.02155  -0.1018   0.8695   0.0711
  -5.750  -0.1771   0.02754   0.01913  -0.1008   0.8634   0.0744
  -5.500  -0.1490   0.02674   0.01826  -0.1011   0.8596   0.0768
  -5.250  -0.1281   0.02616   0.01760  -0.1000   0.8536   0.0791
  -5.000  -0.1063   0.02533   0.01654  -0.0990   0.8478   0.0824
  -4.750  -0.0789   0.02434   0.01525  -0.0989   0.8439   0.0870
  -4.500  -0.0521   0.02398   0.01490  -0.0988   0.8398   0.0908
  -4.250  -0.0331   0.02355   0.01431  -0.0972   0.8329   0.0956
  -4.000  -0.0060   0.02290   0.01350  -0.0970   0.8287   0.1007
  -3.750   0.0244   0.02252   0.01309  -0.0974   0.8255   0.1068
  -3.500   0.0432   0.02224   0.01262  -0.0957   0.8187   0.1131
  -3.250   0.0685   0.02201   0.01245  -0.0952   0.8137   0.1191
  -3.000   0.0989   0.02160   0.01185  -0.0954   0.8102   0.1274
  -2.750   0.1216   0.02147   0.01179  -0.0945   0.8047   0.1334
  -2.500   0.1452   0.02127   0.01148  -0.0935   0.7988   0.1407
  -2.250   0.1747   0.02097   0.01119  -0.0937   0.7947   0.1478
  -2.000   0.2022   0.02073   0.01087  -0.0934   0.7900   0.1556
  -1.750   0.2236   0.02062   0.01077  -0.0921   0.7830   0.1621
  -1.500   0.2540   0.02032   0.01042  -0.0922   0.7783   0.1707
  -1.250   0.2802   0.02010   0.01020  -0.0917   0.7726   0.1783
  -1.000   0.3039   0.01998   0.01006  -0.0907   0.7656   0.1873
  -0.750   0.3353   0.01963   0.00971  -0.0910   0.7609   0.1967
  -0.500   0.3580   0.01956   0.00960  -0.0899   0.7537   0.2071
   0.000   0.4180   0.01897   0.00907  -0.0900   0.7425   0.2321
   0.250   0.4373   0.01897   0.00912  -0.0883   0.7336   0.2440
   0.500   0.4696   0.01868   0.00884  -0.0887   0.7279   0.2613
   0.750   0.4933   0.01862   0.00885  -0.0878   0.7196   0.2786
   1.000   0.5234   0.01839   0.00866  -0.0880   0.7127   0.3007
   1.250   0.5497   0.01822   0.00861  -0.0875   0.7048   0.3302
   1.500   0.5753   0.01789   0.00854  -0.0870   0.6966   0.3931
   2.000   0.7215   0.01645   0.00826  -0.1047   0.6772   1.0000
   2.250   0.7399   0.01659   0.00834  -0.1027   0.6651   1.0000
   2.500   0.7609   0.01665   0.00832  -0.1010   0.6532   1.0000
   2.750   0.7833   0.01667   0.00826  -0.0996   0.6411   1.0000
   3.000   0.8041   0.01672   0.00824  -0.0979   0.6277   1.0000
   3.250   0.8228   0.01684   0.00832  -0.0959   0.6130   1.0000
   3.500   0.8421   0.01695   0.00838  -0.0940   0.5977   1.0000
   3.750   0.8616   0.01706   0.00842  -0.0922   0.5819   1.0000
   4.000   0.8814   0.01718   0.00846  -0.0903   0.5653   1.0000
   4.250   0.9011   0.01732   0.00852  -0.0885   0.5480   1.0000
   4.500   0.9199   0.01751   0.00861  -0.0866   0.5292   1.0000
   4.750   0.9380   0.01775   0.00874  -0.0845   0.5101   1.0000
   5.000   0.9556   0.01803   0.00890  -0.0824   0.4904   1.0000
   5.250   0.9724   0.01836   0.00911  -0.0802   0.4711   1.0000
   5.500   0.9885   0.01873   0.00936  -0.0780   0.4526   1.0000
   5.750   1.0041   0.01914   0.00966  -0.0757   0.4354   1.0000
   6.000   1.0192   0.01958   0.01001  -0.0733   0.4192   1.0000
   6.250   1.0340   0.02004   0.01039  -0.0710   0.4039   1.0000
   6.500   1.0486   0.02052   0.01080  -0.0686   0.3897   1.0000
   6.750   1.0620   0.02101   0.01123  -0.0661   0.3761   1.0000
   7.000   1.0748   0.02151   0.01168  -0.0635   0.3635   1.0000
   7.250   1.0874   0.02205   0.01214  -0.0609   0.3515   1.0000
   7.500   1.1004   0.02259   0.01266  -0.0585   0.3399   1.0000
   7.750   1.1141   0.02315   0.01320  -0.0562   0.3294   1.0000
   8.000   1.1279   0.02375   0.01374  -0.0541   0.3201   1.0000
   8.250   1.1425   0.02434   0.01435  -0.0521   0.3109   1.0000
   8.500   1.1575   0.02497   0.01493  -0.0502   0.3034   1.0000
   8.750   1.1728   0.02559   0.01560  -0.0485   0.2955   1.0000
   9.000   1.1882   0.02626   0.01623  -0.0468   0.2890   1.0000
   9.250   1.2038   0.02691   0.01696  -0.0452   0.2820   1.0000
   9.500   1.2191   0.02760   0.01766  -0.0435   0.2759   1.0000
   9.750   1.2351   0.02831   0.01838  -0.0420   0.2701   1.0000
  10.000   1.2501   0.02904   0.01920  -0.0405   0.2641   1.0000
  10.250   1.2660   0.02977   0.01993  -0.0391   0.2592   1.0000
  10.500   1.2819   0.03054   0.02075  -0.0377   0.2542   1.0000
  10.750   1.2955   0.03135   0.02167  -0.0361   0.2487   1.0000
  11.000   1.3099   0.03215   0.02249  -0.0346   0.2439   1.0000
  11.250   1.3235   0.03301   0.02342  -0.0331   0.2390   1.0000
  11.500   1.3345   0.03395   0.02449  -0.0314   0.2336   1.0000
  11.750   1.3475   0.03484   0.02544  -0.0300   0.2292   1.0000
  12.000   1.3616   0.03573   0.02635  -0.0287   0.2250   1.0000
  12.250   1.3691   0.03688   0.02770  -0.0269   0.2199   1.0000
  12.500   1.3762   0.03798   0.02888  -0.0251   0.2144   1.0000
  12.750   1.3826   0.03917   0.03011  -0.0234   0.2088   1.0000
  13.000   1.3850   0.04062   0.03174  -0.0215   0.2028   1.0000
  13.250   1.3888   0.04197   0.03311  -0.0199   0.1970   1.0000
  13.500   1.3903   0.04365   0.03495  -0.0183   0.1912   1.0000
  13.750   1.3922   0.04534   0.03679  -0.0168   0.1856   1.0000
  14.000   1.3941   0.04703   0.03850  -0.0155   0.1802   1.0000
  14.250   1.3935   0.04914   0.04084  -0.0143   0.1744   1.0000
  14.500   1.3929   0.05123   0.04304  -0.0133   0.1690   1.0000
  14.750   1.3915   0.05354   0.04547  -0.0124   0.1635   1.0000
  15.000   1.3877   0.05623   0.04835  -0.0117   0.1571   1.0000
  15.250   1.3847   0.05887   0.05104  -0.0112   0.1520   1.0000
  15.500   1.3800   0.06203   0.05447  -0.0110   0.1456   1.0000
  15.750   1.3720   0.06555   0.05808  -0.0110   0.1390   1.0000
  16.000   1.3637   0.06950   0.06226  -0.0113   0.1314   1.0000
  16.250   1.3528   0.07384   0.06673  -0.0120   0.1245   1.0000
  16.500   1.3394   0.07883   0.07189  -0.0130   0.1157   1.0000
  16.750   1.3228   0.08449   0.07768  -0.0146   0.1066   1.0000
  17.000   1.3028   0.09088   0.08414  -0.0166   0.0988   1.0000
  17.250   1.2821   0.09762   0.09095  -0.0190   0.0929   1.0000
  17.500   1.2602   0.10479   0.09820  -0.0217   0.0872   1.0000
  17.750   1.2390   0.11203   0.10553  -0.0247   0.0823   1.0000
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