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CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CURTISS CR-1 AIRFOIL (cr1-il)
Reynolds number: 50,000
Max Cl/Cd: 32.44 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cr1-il-50000-n5.txt
Download as CSV file: xf-cr1-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3432   0.11223   0.10548  -0.0367   1.0000   0.0983
  -8.750  -0.3424   0.11003   0.10333  -0.0340   1.0000   0.0972
  -8.500  -0.3486   0.10814   0.10150  -0.0317   1.0000   0.0958
  -8.250  -0.3412   0.10442   0.09778  -0.0342   0.9952   0.0937
  -8.000  -0.3338   0.10023   0.09359  -0.0383   0.9878   0.0919
  -7.750  -0.3279   0.09627   0.08962  -0.0425   0.9803   0.0915
  -7.500  -0.3245   0.09266   0.08601  -0.0461   0.9717   0.0920
  -7.250  -0.3218   0.08891   0.08224  -0.0496   0.9627   0.0922
  -7.000  -0.3123   0.08435   0.07764  -0.0549   0.9552   0.0925
  -6.750  -0.3103   0.08024   0.07348  -0.0579   0.9456   0.0920
  -6.500  -0.3000   0.07534   0.06848  -0.0629   0.9389   0.0916
  -6.250  -0.2973   0.07130   0.06434  -0.0650   0.9298   0.0916
  -6.000  -0.2821   0.06663   0.05948  -0.0695   0.9242   0.0933
  -5.750  -0.2800   0.06280   0.05547  -0.0704   0.9153   0.0949
  -5.500  -0.2662   0.05731   0.04960  -0.0740   0.9094   0.0967
  -5.250  -0.2607   0.05260   0.04443  -0.0747   0.9019   0.0978
  -5.000  -0.2456   0.04926   0.04076  -0.0752   0.8959   0.0996
  -4.750  -0.2174   0.04839   0.03986  -0.0762   0.8920   0.1029
  -4.500  -0.2067   0.04669   0.03793  -0.0747   0.8846   0.1060
  -4.250  -0.1879   0.04361   0.03429  -0.0749   0.8792   0.1102
  -4.000  -0.1605   0.04121   0.03145  -0.0760   0.8753   0.1144
  -3.750  -0.1473   0.04081   0.03102  -0.0740   0.8679   0.1180
  -3.500  -0.1238   0.03928   0.02907  -0.0739   0.8626   0.1248
  -3.250  -0.0926   0.03812   0.02767  -0.0749   0.8588   0.1310
  -3.000  -0.0789   0.03772   0.02715  -0.0728   0.8512   0.1368
  -2.750  -0.0526   0.03673   0.02584  -0.0728   0.8458   0.1446
  -2.500  -0.0190   0.03615   0.02511  -0.0739   0.8419   0.1539
  -2.250  -0.0052   0.03576   0.02453  -0.0718   0.8337   0.1603
  -2.000   0.0243   0.03536   0.02402  -0.0722   0.8283   0.1700
  -1.750   0.0610   0.03476   0.02326  -0.0737   0.8246   0.1800
  -1.500   0.0739   0.03469   0.02303  -0.0713   0.8151   0.1880
  -1.250   0.1091   0.03420   0.02248  -0.0725   0.8104   0.1980
  -1.000   0.1308   0.03408   0.02216  -0.0716   0.8025   0.2081
  -0.750   0.1631   0.03378   0.02182  -0.0723   0.7962   0.2192
  -0.500   0.2080   0.03325   0.02120  -0.0749   0.7924   0.2333
  -0.250   0.2240   0.03338   0.02126  -0.0732   0.7820   0.2437
   0.000   0.2665   0.03288   0.02071  -0.0753   0.7774   0.2601
   0.250   0.2859   0.03296   0.02078  -0.0740   0.7676   0.2745
   0.500   0.3245   0.03246   0.02036  -0.0755   0.7620   0.2961
   0.750   0.3470   0.03240   0.02037  -0.0746   0.7528   0.3158
   1.000   0.3818   0.03190   0.02003  -0.0755   0.7462   0.3479
   1.500   0.4999   0.02979   0.01965  -0.0868   0.7323   1.0000
   1.750   0.5411   0.02944   0.01903  -0.0881   0.7268   1.0000
   2.000   0.5537   0.02990   0.01937  -0.0854   0.7142   1.0000
   2.250   0.5793   0.02996   0.01929  -0.0845   0.7049   1.0000
   2.500   0.6081   0.02987   0.01908  -0.0840   0.6957   1.0000
   2.750   0.6247   0.03017   0.01931  -0.0818   0.6835   1.0000
   3.000   0.6649   0.02964   0.01866  -0.0827   0.6767   1.0000
   3.250   0.6780   0.03000   0.01897  -0.0800   0.6629   1.0000
   3.500   0.6950   0.03021   0.01914  -0.0778   0.6497   1.0000
   3.750   0.7186   0.03015   0.01903  -0.0765   0.6379   1.0000
   4.000   0.7515   0.02968   0.01849  -0.0762   0.6278   1.0000
   4.500   0.7834   0.02999   0.01876  -0.0714   0.5986   1.0000
   4.750   0.8013   0.03005   0.01879  -0.0692   0.5841   1.0000
   5.000   0.8208   0.03005   0.01877  -0.0672   0.5695   1.0000
   5.250   0.8417   0.03003   0.01872  -0.0655   0.5549   1.0000
   5.500   0.8638   0.02999   0.01863  -0.0639   0.5400   1.0000
   5.750   0.8863   0.02998   0.01856  -0.0624   0.5249   1.0000
   6.000   0.9087   0.03001   0.01855  -0.0610   0.5093   1.0000
   6.250   0.9310   0.03011   0.01859  -0.0595   0.4937   1.0000
   6.500   0.9529   0.03030   0.01870  -0.0581   0.4783   1.0000
   6.750   0.9737   0.03057   0.01891  -0.0567   0.4628   1.0000
   7.000   0.9944   0.03092   0.01918  -0.0552   0.4478   1.0000
   7.250   1.0156   0.03131   0.01948  -0.0539   0.4336   1.0000
   7.500   1.0325   0.03192   0.02006  -0.0522   0.4195   1.0000
   7.750   1.0476   0.03265   0.02077  -0.0504   0.4060   1.0000
   8.000   1.0642   0.03337   0.02147  -0.0488   0.3935   1.0000
   8.250   1.0846   0.03401   0.02206  -0.0476   0.3824   1.0000
   8.500   1.1027   0.03477   0.02284  -0.0463   0.3718   1.0000
   8.750   1.1178   0.03571   0.02382  -0.0447   0.3617   1.0000
   9.000   1.1425   0.03628   0.02433  -0.0442   0.3525   1.0000
   9.250   1.1521   0.03746   0.02563  -0.0421   0.3430   1.0000
   9.500   1.1757   0.03815   0.02632  -0.0415   0.3352   1.0000
   9.750   1.1862   0.03939   0.02771  -0.0397   0.3271   1.0000
  10.000   1.2164   0.03994   0.02822  -0.0399   0.3207   1.0000
  10.250   1.2201   0.04156   0.03005  -0.0375   0.3139   1.0000
  10.500   1.2390   0.04253   0.03110  -0.0366   0.3076   1.0000
  10.750   1.2543   0.04372   0.03239  -0.0354   0.3017   1.0000
  11.000   1.2591   0.04540   0.03425  -0.0333   0.2958   1.0000
  11.250   1.2809   0.04633   0.03525  -0.0327   0.2907   1.0000
  11.500   1.2900   0.04796   0.03706  -0.0312   0.2860   1.0000
  11.750   1.2848   0.05031   0.03963  -0.0287   0.2810   1.0000
  12.000   1.3001   0.05145   0.04085  -0.0276   0.2756   1.0000
  12.250   1.3064   0.05315   0.04267  -0.0261   0.2706   1.0000
  12.500   1.2851   0.05671   0.04649  -0.0234   0.2656   1.0000
  12.750   1.2928   0.05838   0.04826  -0.0221   0.2606   1.0000
  13.000   1.3091   0.05949   0.04946  -0.0212   0.2559   1.0000
  13.250   1.2541   0.06668   0.05693  -0.0192   0.2519   1.0000
  13.500   1.2065   0.07449   0.06492  -0.0190   0.2471   1.0000
  13.750   1.2434   0.07319   0.06373  -0.0178   0.2432   1.0000
  14.000   1.0410   0.10629   0.09684  -0.0288   0.2304   1.0000
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