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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 50,000
Max Cl/Cd: 35.89 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg12a-il-50000-n5.txt
Download as CSV file: xf-rg12a-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4943   0.09080   0.08379  -0.0332   1.0000   0.0408
  -8.750  -0.4943   0.08696   0.08001  -0.0340   1.0000   0.0403
  -8.500  -0.4986   0.08268   0.07580  -0.0358   1.0000   0.0398
  -8.250  -0.5056   0.07870   0.07189  -0.0371   1.0000   0.0393
  -8.000  -0.5116   0.07458   0.06780  -0.0382   1.0000   0.0389
  -7.750  -0.5175   0.07035   0.06356  -0.0391   1.0000   0.0384
  -7.500  -0.5219   0.06619   0.05934  -0.0396   1.0000   0.0380
  -7.250  -0.5246   0.06197   0.05501  -0.0398   1.0000   0.0376
  -7.000  -0.5247   0.05779   0.05064  -0.0396   1.0000   0.0372
  -6.750  -0.5218   0.05370   0.04631  -0.0393   1.0000   0.0369
  -6.500  -0.5158   0.04965   0.04188  -0.0386   1.0000   0.0368
  -6.250  -0.5065   0.04584   0.03769  -0.0378   1.0000   0.0368
  -6.000  -0.4941   0.04223   0.03363  -0.0368   1.0000   0.0371
  -5.750  -0.4788   0.03898   0.02987  -0.0358   1.0000   0.0387
  -5.500  -0.4606   0.03609   0.02633  -0.0346   1.0000   0.0407
  -5.250  -0.4422   0.03342   0.02339  -0.0336   1.0000   0.0431
  -5.000  -0.4217   0.03123   0.02093  -0.0325   1.0000   0.0452
  -4.750  -0.3997   0.02917   0.01855  -0.0313   1.0000   0.0479
  -4.500  -0.3767   0.02750   0.01645  -0.0299   1.0000   0.0533
  -4.250  -0.3558   0.02601   0.01495  -0.0287   1.0000   0.0609
  -4.000  -0.3336   0.02453   0.01329  -0.0271   1.0000   0.0687
  -3.750  -0.3124   0.02335   0.01211  -0.0259   1.0000   0.0864
  -3.500  -0.2908   0.02210   0.01091  -0.0249   1.0000   0.1183
  -3.250  -0.2705   0.02076   0.00993  -0.0240   1.0000   0.1791
  -3.000  -0.2515   0.01916   0.00912  -0.0233   1.0000   0.3092
  -2.750  -0.2415   0.01765   0.00904  -0.0194   1.0000   0.5694
  -2.500  -0.2353   0.01756   0.00939  -0.0130   1.0000   0.7678
  -2.250  -0.2228   0.01760   0.00938  -0.0083   1.0000   0.8578
  -2.000  -0.1679   0.01770   0.00915  -0.0115   1.0000   0.9511
  -1.750  -0.0934   0.01769   0.00859  -0.0207   1.0000   1.0000
  -1.500  -0.0901   0.01759   0.00834  -0.0174   1.0000   1.0000
  -1.250  -0.0834   0.01755   0.00814  -0.0147   1.0000   1.0000
  -1.000  -0.0723   0.01759   0.00801  -0.0129   1.0000   1.0000
  -0.750  -0.0438   0.01781   0.00802  -0.0142   0.9946   1.0000
  -0.500   0.0000   0.01813   0.00809  -0.0182   0.9829   1.0000
  -0.250   0.0426   0.01839   0.00818  -0.0219   0.9704   1.0000
   0.000   0.0838   0.01860   0.00824  -0.0252   0.9573   1.0000
   0.250   0.1240   0.01877   0.00828  -0.0282   0.9436   1.0000
   0.500   0.1636   0.01890   0.00833  -0.0309   0.9294   1.0000
   0.750   0.2025   0.01899   0.00838  -0.0333   0.9148   1.0000
   1.000   0.2410   0.01905   0.00841  -0.0356   0.8998   1.0000
   1.250   0.2796   0.01908   0.00843  -0.0377   0.8845   1.0000
   1.500   0.3180   0.01908   0.00846  -0.0397   0.8687   1.0000
   1.750   0.3547   0.01907   0.00849  -0.0412   0.8521   1.0000
   2.000   0.3914   0.01903   0.00850  -0.0426   0.8351   1.0000
   2.250   0.4283   0.01897   0.00849  -0.0439   0.8178   1.0000
   2.500   0.4585   0.01901   0.00861  -0.0440   0.7966   1.0000
   2.750   0.4925   0.01897   0.00863  -0.0445   0.7765   1.0000
   3.000   0.5218   0.01903   0.00874  -0.0443   0.7536   1.0000
   3.250   0.5528   0.01907   0.00883  -0.0443   0.7307   1.0000
   3.500   0.5818   0.01917   0.00902  -0.0439   0.7061   1.0000
   3.750   0.6089   0.01934   0.00924  -0.0432   0.6798   1.0000
   4.000   0.6354   0.01954   0.00948  -0.0424   0.6526   1.0000
   4.250   0.6610   0.01978   0.00977  -0.0415   0.6242   1.0000
   4.500   0.6858   0.02007   0.01013  -0.0404   0.5945   1.0000
   4.750   0.7099   0.02039   0.01048  -0.0393   0.5639   1.0000
   5.000   0.7327   0.02076   0.01089  -0.0380   0.5313   1.0000
   5.250   0.7547   0.02118   0.01134  -0.0366   0.4970   1.0000
   5.500   0.7762   0.02165   0.01185  -0.0351   0.4618   1.0000
   5.750   0.7965   0.02219   0.01240  -0.0336   0.4243   1.0000
   6.000   0.8160   0.02280   0.01301  -0.0320   0.3854   1.0000
   6.250   0.8345   0.02351   0.01369  -0.0304   0.3450   1.0000
   6.500   0.8519   0.02434   0.01447  -0.0288   0.3031   1.0000
   6.750   0.8683   0.02531   0.01536  -0.0271   0.2603   1.0000
   7.000   0.8835   0.02647   0.01647  -0.0255   0.2176   1.0000
   7.250   0.8977   0.02784   0.01771  -0.0238   0.1765   1.0000
   7.500   0.9105   0.02944   0.01912  -0.0222   0.1395   1.0000
   7.750   0.9231   0.03117   0.02074  -0.0206   0.1084   1.0000
   8.000   0.9351   0.03304   0.02249  -0.0190   0.0887   1.0000
   8.250   0.9487   0.03494   0.02446  -0.0174   0.0742   1.0000
   8.500   0.9635   0.03697   0.02659  -0.0159   0.0660   1.0000
   8.750   0.9819   0.03925   0.02917  -0.0146   0.0599   1.0000
   9.000   0.9966   0.04128   0.03133  -0.0134   0.0544   1.0000
   9.250   1.0122   0.04375   0.03403  -0.0123   0.0501   1.0000
   9.500   1.0276   0.04660   0.03730  -0.0111   0.0472   1.0000
   9.750   1.0393   0.04964   0.04069  -0.0097   0.0453   1.0000
  10.000   1.0469   0.05277   0.04414  -0.0083   0.0439   1.0000
  10.250   1.0505   0.05605   0.04769  -0.0067   0.0428   1.0000
  10.500   1.0496   0.05937   0.05125  -0.0050   0.0419   1.0000
  10.750   1.0454   0.06306   0.05508  -0.0035   0.0411   1.0000
  11.000   1.0313   0.06677   0.05912  -0.0020   0.0408   1.0000
  11.250   1.0145   0.07094   0.06358  -0.0015   0.0407   1.0000
  11.500   0.9965   0.07568   0.06856  -0.0023   0.0406   1.0000
  11.750   0.9787   0.08099   0.07406  -0.0042   0.0408   1.0000
  12.000   0.9589   0.08718   0.08041  -0.0075   0.0409   1.0000
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