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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.51 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12a-il-1000000-n5.txt
Download as CSV file: xf-rg12a-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL PROFILE12A 9.00%                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5255   0.08873   0.08709  -0.0241   1.0000   0.0027
  -9.750  -0.5376   0.08237   0.08076  -0.0269   1.0000   0.0026
  -8.750  -0.7114   0.02620   0.02320  -0.0466   0.9957   0.0029
  -8.500  -0.6881   0.02264   0.01920  -0.0481   0.9938   0.0030
  -8.250  -0.6645   0.02040   0.01664  -0.0486   0.9914   0.0031
  -8.000  -0.6389   0.01837   0.01431  -0.0492   0.9891   0.0032
  -7.750  -0.6108   0.01692   0.01262  -0.0500   0.9873   0.0033
  -7.500  -0.5815   0.01554   0.01102  -0.0509   0.9857   0.0033
  -7.250  -0.5506   0.01454   0.00985  -0.0520   0.9844   0.0034
  -7.000  -0.5188   0.01369   0.00886  -0.0533   0.9833   0.0036
  -6.750  -0.4955   0.01298   0.00804  -0.0525   0.9791   0.0036
  -6.500  -0.4664   0.01252   0.00752  -0.0530   0.9763   0.0038
  -6.250  -0.4366   0.01179   0.00669  -0.0536   0.9739   0.0039
  -6.000  -0.4062   0.01082   0.00558  -0.0545   0.9719   0.0042
  -5.750  -0.3766   0.01022   0.00490  -0.0550   0.9692   0.0044
  -5.500  -0.3511   0.00978   0.00441  -0.0546   0.9633   0.0047
  -5.250  -0.3195   0.00938   0.00397  -0.0555   0.9595   0.0050
  -5.000  -0.2885   0.00903   0.00358  -0.0562   0.9548   0.0056
  -4.750  -0.2576   0.00870   0.00321  -0.0569   0.9483   0.0061
  -4.500  -0.2240   0.00837   0.00283  -0.0582   0.9421   0.0068
  -4.250  -0.1914   0.00807   0.00249  -0.0593   0.9327   0.0083
  -4.000  -0.1593   0.00785   0.00223  -0.0602   0.9208   0.0103
  -3.750  -0.1291   0.00762   0.00197  -0.0607   0.9055   0.0148
  -3.500  -0.1009   0.00740   0.00174  -0.0608   0.8878   0.0281
  -3.250  -0.0738   0.00725   0.00158  -0.0606   0.8675   0.0428
  -2.750  -0.0218   0.00695   0.00130  -0.0598   0.8236   0.0941
  -2.500   0.0038   0.00680   0.00118  -0.0594   0.8006   0.1297
  -2.250   0.0293   0.00668   0.00108  -0.0590   0.7762   0.1688
  -2.000   0.0547   0.00649   0.00099  -0.0586   0.7525   0.2255
  -1.750   0.0803   0.00635   0.00092  -0.0582   0.7289   0.2805
  -1.500   0.1061   0.00624   0.00085  -0.0579   0.7060   0.3289
  -1.250   0.1320   0.00608   0.00080  -0.0576   0.6843   0.3929
  -1.000   0.1573   0.00580   0.00075  -0.0573   0.6631   0.4952
  -0.750   0.1824   0.00546   0.00073  -0.0569   0.6429   0.6176
  -0.500   0.2083   0.00538   0.00076  -0.0565   0.6221   0.6881
  -0.250   0.2350   0.00543   0.00079  -0.0563   0.6022   0.7172
   0.000   0.2619   0.00549   0.00082  -0.0560   0.5818   0.7351
   0.250   0.2887   0.00558   0.00086  -0.0558   0.5618   0.7488
   0.500   0.3158   0.00568   0.00089  -0.0556   0.5411   0.7601
   0.750   0.3426   0.00578   0.00094  -0.0553   0.5200   0.7704
   1.000   0.3694   0.00589   0.00099  -0.0551   0.4973   0.7799
   1.250   0.3963   0.00602   0.00105  -0.0549   0.4749   0.7892
   1.500   0.4229   0.00614   0.00112  -0.0546   0.4527   0.7997
   1.750   0.4493   0.00626   0.00120  -0.0543   0.4305   0.8106
   2.000   0.4759   0.00641   0.00128  -0.0541   0.4080   0.8191
   2.250   0.5024   0.00657   0.00138  -0.0538   0.3830   0.8249
   2.500   0.5289   0.00676   0.00147  -0.0536   0.3571   0.8294
   2.750   0.5554   0.00693   0.00157  -0.0534   0.3349   0.8333
   3.000   0.5818   0.00712   0.00170  -0.0532   0.3108   0.8378
   3.250   0.6079   0.00734   0.00183  -0.0529   0.2841   0.8425
   3.500   0.6337   0.00760   0.00198  -0.0526   0.2539   0.8469
   3.750   0.6589   0.00789   0.00215  -0.0522   0.2207   0.8521
   4.000   0.6830   0.00833   0.00239  -0.0517   0.1718   0.8580
   4.250   0.7079   0.00866   0.00260  -0.0512   0.1421   0.8636
   4.500   0.7332   0.00893   0.00281  -0.0508   0.1198   0.8699
   4.750   0.7583   0.00922   0.00304  -0.0504   0.0997   0.8763
   5.000   0.7829   0.00954   0.00329  -0.0499   0.0796   0.8840
   5.250   0.8070   0.00988   0.00358  -0.0493   0.0586   0.8926
   5.500   0.8309   0.01022   0.00386  -0.0486   0.0431   0.9029
   6.000   0.8763   0.01089   0.00449  -0.0467   0.0183   0.9314
   6.250   0.8992   0.01115   0.00480  -0.0457   0.0141   0.9561
   6.500   0.9296   0.01147   0.00515  -0.0465   0.0124   1.0000
   6.750   0.9546   0.01182   0.00553  -0.0461   0.0112   1.0000
   7.000   0.9793   0.01221   0.00596  -0.0456   0.0104   1.0000
   7.250   1.0035   0.01265   0.00646  -0.0451   0.0098   1.0000
   7.500   1.0281   0.01301   0.00687  -0.0447   0.0097   1.0000
   7.750   1.0523   0.01341   0.00733  -0.0442   0.0095   1.0000
   8.000   1.0763   0.01381   0.00777  -0.0437   0.0092   1.0000
   8.250   1.1001   0.01421   0.00822  -0.0431   0.0087   1.0000
   8.500   1.1237   0.01462   0.00867  -0.0426   0.0082   1.0000
   8.750   1.1469   0.01506   0.00915  -0.0420   0.0077   1.0000
   9.000   1.1695   0.01555   0.00968  -0.0413   0.0073   1.0000
   9.250   1.1910   0.01614   0.01034  -0.0405   0.0069   1.0000
   9.500   1.2096   0.01702   0.01133  -0.0392   0.0063   1.0000
   9.750   1.2317   0.01748   0.01183  -0.0385   0.0061   1.0000
  10.000   1.2538   0.01792   0.01233  -0.0378   0.0059   1.0000
  10.250   1.2752   0.01840   0.01287  -0.0370   0.0056   1.0000
  10.500   1.2964   0.01887   0.01339  -0.0362   0.0052   1.0000
  10.750   1.3168   0.01939   0.01396  -0.0352   0.0048   1.0000
  11.000   1.3370   0.01990   0.01451  -0.0343   0.0045   1.0000
  11.250   1.3558   0.02049   0.01516  -0.0332   0.0042   1.0000
  11.500   1.3723   0.02126   0.01598  -0.0318   0.0038   1.0000
  11.750   1.3886   0.02197   0.01677  -0.0303   0.0036   1.0000
  12.000   1.4029   0.02269   0.01758  -0.0286   0.0034   1.0000
  12.250   1.4151   0.02340   0.01837  -0.0264   0.0033   1.0000
  12.500   1.4258   0.02418   0.01923  -0.0241   0.0030   1.0000
  12.750   1.4360   0.02501   0.02013  -0.0219   0.0028   1.0000
  13.000   1.4447   0.02593   0.02113  -0.0197   0.0026   1.0000
  13.250   1.4533   0.02690   0.02215  -0.0176   0.0024   1.0000
  13.500   1.4584   0.02813   0.02349  -0.0153   0.0023   1.0000
  13.750   1.4611   0.02960   0.02508  -0.0130   0.0022   1.0000
  14.000   1.4606   0.03141   0.02701  -0.0108   0.0021   1.0000
  14.250   1.4615   0.03322   0.02894  -0.0092   0.0020   1.0000
  14.500   1.4618   0.03523   0.03107  -0.0079   0.0019   1.0000
  14.750   1.4591   0.03768   0.03366  -0.0069   0.0019   1.0000
  15.000   1.4552   0.04050   0.03661  -0.0064   0.0019   1.0000
  15.250   1.4517   0.04352   0.03976  -0.0065   0.0018   1.0000
  15.500   1.4451   0.04717   0.04354  -0.0071   0.0018   1.0000
  15.750   1.4351   0.05160   0.04812  -0.0084   0.0018   1.0000
  16.000   1.4238   0.05655   0.05322  -0.0104   0.0017   1.0000
  16.250   1.4110   0.06211   0.05892  -0.0130   0.0017   1.0000
  16.500   1.3914   0.06918   0.06616  -0.0166   0.0017   1.0000
  16.750   1.3740   0.07628   0.07341  -0.0205   0.0017   1.0000
  17.000   1.3509   0.08486   0.08214  -0.0254   0.0017   1.0000
  17.250   1.3189   0.09566   0.09312  -0.0316   0.0017   1.0000
  17.500   1.2894   0.10638   0.10400  -0.0378   0.0018   1.0000
  17.750   1.2528   0.11915   0.11693  -0.0453   0.0018   1.0000
  18.000   1.2202   0.13141   0.12933  -0.0524   0.0019   1.0000
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