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CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CURTISS CR-1 AIRFOIL (cr1-il)
Reynolds number: 50,000
Max Cl/Cd: 22.74 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-cr1-il-50000.txt
Download as CSV file: xf-cr1-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2632   0.13058   0.12331  -0.0382   1.0000   0.1842
 -10.500  -0.2724   0.12999   0.12282  -0.0380   1.0000   0.1885
 -10.250  -0.2983   0.13186   0.12487  -0.0380   1.0000   0.1902
 -10.000  -0.2762   0.12520   0.11821  -0.0363   1.0000   0.1933
  -9.750  -0.2702   0.12239   0.11545  -0.0344   1.0000   0.1984
  -9.500  -0.2805   0.12161   0.11477  -0.0327   1.0000   0.2036
  -9.250  -0.3063   0.12275   0.11607  -0.0308   1.0000   0.2061
  -9.000  -0.3385   0.12445   0.11794  -0.0285   1.0000   0.2069
  -8.750  -0.3023   0.11685   0.11029  -0.0262   1.0000   0.2129
  -8.500  -0.3109   0.11569   0.10921  -0.0238   1.0000   0.2177
  -8.250  -0.3334   0.11594   0.10958  -0.0214   1.0000   0.2216
  -8.000  -0.3688   0.11743   0.11123  -0.0190   1.0000   0.2232
  -7.750  -0.3588   0.11306   0.10689  -0.0171   1.0000   0.2261
  -7.500  -0.3534   0.11034   0.10418  -0.0148   1.0000   0.2310
  -7.250  -0.3680   0.10941   0.10333  -0.0125   1.0000   0.2358
  -7.000  -0.4023   0.11004   0.10410  -0.0098   1.0000   0.2390
  -6.750  -0.4452   0.11110   0.10530  -0.0076   1.0000   0.2402
  -6.500  -0.4046   0.10471   0.09886  -0.0055   1.0000   0.2476
  -6.250  -0.4250   0.10382   0.09805  -0.0027   1.0000   0.2528
  -6.000  -0.4614   0.10393   0.09826  -0.0028   1.0000   0.2565
  -5.750  -0.4463   0.09969   0.09405   0.0007   1.0000   0.2624
  -5.500  -0.4575   0.09805   0.09244   0.0018   1.0000   0.2706
  -5.250  -0.4691   0.09563   0.09008   0.0020   1.0000   0.2762
  -5.000  -0.4651   0.09305   0.08752   0.0046   1.0000   0.2841
  -4.750  -0.4762   0.09071   0.08520   0.0037   1.0000   0.2927
  -4.500  -0.4719   0.08808   0.08259   0.0063   1.0000   0.3011
  -4.250  -0.4750   0.08540   0.07992   0.0063   1.0000   0.3112
  -4.000  -0.4762   0.08308   0.07757   0.0057   1.0000   0.3256
  -3.750  -0.4741   0.08079   0.07526   0.0061   1.0000   0.3416
  -3.500  -0.4709   0.07827   0.07275   0.0079   1.0000   0.3587
  -3.250  -0.4677   0.07563   0.07016   0.0109   1.0000   0.3770
  -3.000  -0.4645   0.07319   0.06777   0.0143   1.0000   0.3974
  -2.750  -0.4636   0.07106   0.06567   0.0170   1.0000   0.4287
  -2.500  -0.4637   0.06894   0.06361   0.0213   1.0000   0.4626
  -2.000  -0.3369   0.05643   0.04917  -0.0181   1.0000   0.2576
  -1.750  -0.3075   0.05181   0.04391  -0.0213   1.0000   0.2251
  -1.500  -0.2858   0.04971   0.04133  -0.0219   1.0000   0.2233
  -1.250  -0.2714   0.04824   0.03990  -0.0210   1.0000   0.2287
  -1.000  -0.2523   0.04677   0.03814  -0.0210   1.0000   0.2308
  -0.750  -0.2328   0.04565   0.03665  -0.0208   1.0000   0.2370
  -0.500  -0.2144   0.04462   0.03534  -0.0205   1.0000   0.2433
  -0.250  -0.1973   0.04405   0.03463  -0.0200   1.0000   0.2519
   0.000  -0.0937   0.04534   0.03534  -0.0338   0.9561   0.2782
   0.250  -0.0485   0.04541   0.03512  -0.0376   0.9375   0.2935
   0.500  -0.0088   0.04552   0.03501  -0.0404   0.9207   0.3096
   0.750   0.0290   0.04571   0.03507  -0.0427   0.9047   0.3264
   1.000   0.0729   0.04599   0.03520  -0.0461   0.8879   0.3456
   1.250   0.1188   0.04636   0.03547  -0.0499   0.8714   0.3715
   1.500   0.1655   0.04661   0.03576  -0.0536   0.8548   0.4016
   1.750   0.2115   0.04675   0.03614  -0.0571   0.8391   0.4489
   2.000   0.2945   0.04555   0.03659  -0.0677   0.8215   1.0000
   2.250   0.3306   0.04649   0.03701  -0.0691   0.8056   1.0000
   2.500   0.3635   0.04732   0.03754  -0.0700   0.7897   1.0000
   2.750   0.3951   0.04809   0.03810  -0.0707   0.7737   1.0000
   3.000   0.4272   0.04879   0.03863  -0.0712   0.7577   1.0000
   3.250   0.4605   0.04939   0.03910  -0.0718   0.7419   1.0000
   3.500   0.4954   0.04984   0.03944  -0.0724   0.7263   1.0000
   3.750   0.5229   0.05036   0.03988  -0.0721   0.7099   1.0000
   4.000   0.5499   0.05082   0.04028  -0.0715   0.6936   1.0000
   4.250   0.5770   0.05120   0.04061  -0.0709   0.6772   1.0000
   4.500   0.6031   0.05158   0.04094  -0.0702   0.6611   1.0000
   4.750   0.6295   0.05185   0.04119  -0.0693   0.6451   1.0000
   5.000   0.6556   0.05206   0.04137  -0.0683   0.6292   1.0000
   5.250   0.6799   0.05233   0.04163  -0.0672   0.6136   1.0000
   5.500   0.7040   0.05257   0.04188  -0.0660   0.5982   1.0000
   5.750   0.7272   0.05284   0.04214  -0.0647   0.5831   1.0000
   6.500   0.8194   0.05164   0.04100  -0.0615   0.5445   1.0000
   6.750   0.8603   0.05013   0.03952  -0.0606   0.5335   1.0000
   7.000   0.8704   0.05143   0.04085  -0.0586   0.5189   1.0000
   7.250   0.8785   0.05306   0.04249  -0.0566   0.5048   1.0000
   7.500   1.0134   0.04467   0.03419  -0.0619   0.5002   1.0000
   7.750   0.9816   0.04887   0.03840  -0.0565   0.4861   1.0000
   8.000   0.9325   0.05579   0.04532  -0.0524   0.4712   1.0000
   8.250   1.0734   0.04721   0.03684  -0.0579   0.4652   1.0000
   8.500   0.9806   0.05682   0.04645  -0.0503   0.4529   1.0000
   8.750   0.8664   0.07340   0.06297  -0.0497   0.4376   1.0000
   9.000   0.9888   0.06216   0.05187  -0.0476   0.4349   1.0000
   9.250   0.8044   0.08835   0.07793  -0.0508   0.4259   1.0000
   9.500   0.7919   0.09390   0.08350  -0.0514   0.4238   1.0000
   9.750   0.8302   0.09381   0.08348  -0.0504   0.4174   1.0000
  10.000   0.8054   0.10083   0.09052  -0.0517   0.4168   1.0000
  10.250   0.7991   0.10609   0.09582  -0.0526   0.4173   1.0000
  10.500   0.6519   0.12655   0.11636  -0.0629   0.5397   1.0000
  10.750   0.6759   0.13013   0.12000  -0.0637   0.5326   1.0000
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