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AIRFOIL PROFILE12A 9.00% (rg12a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL PROFILE12A 9.00% (rg12a-il)
Reynolds number: 200,000
Max Cl/Cd: 67.06 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg12a-il-200000.txt
Download as CSV file: xf-rg12a-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4777   0.08764   0.08413  -0.0273   1.0000   0.0460
  -8.500  -0.4811   0.08385   0.08038  -0.0289   1.0000   0.0470
  -8.250  -0.4888   0.07976   0.07637  -0.0310   1.0000   0.0482
  -8.000  -0.5024   0.07569   0.07237  -0.0333   1.0000   0.0486
  -7.750  -0.5129   0.07114   0.06782  -0.0361   1.0000   0.0493
  -7.250  -0.5346   0.06339   0.05955  -0.0398   1.0000   0.0523
  -7.000  -0.5413   0.05668   0.05276  -0.0394   1.0000   0.0534
  -6.750  -0.5325   0.05320   0.04937  -0.0382   1.0000   0.0545
  -6.500  -0.5242   0.05059   0.04675  -0.0368   1.0000   0.0560
  -6.250  -0.5161   0.04783   0.04390  -0.0356   1.0000   0.0582
  -6.000  -0.5069   0.04478   0.04062  -0.0345   1.0000   0.0620
  -5.250  -0.4614   0.02824   0.02197  -0.0288   1.0000   0.0295
  -5.000  -0.4423   0.02415   0.01753  -0.0278   1.0000   0.0281
  -4.750  -0.4203   0.02170   0.01470  -0.0267   1.0000   0.0278
  -4.500  -0.3979   0.02089   0.01358  -0.0255   1.0000   0.0295
  -4.250  -0.3745   0.01830   0.01078  -0.0248   1.0000   0.0313
  -4.000  -0.3511   0.01699   0.00937  -0.0238   1.0000   0.0326
  -3.750  -0.3282   0.01602   0.00835  -0.0229   1.0000   0.0347
  -3.500  -0.3055   0.01522   0.00747  -0.0219   1.0000   0.0386
  -3.250  -0.2832   0.01438   0.00667  -0.0212   1.0000   0.0481
  -3.000  -0.2599   0.01339   0.00577  -0.0205   1.0000   0.0770
  -2.750  -0.2247   0.01222   0.00530  -0.0230   0.9967   0.2131
  -2.500  -0.1918   0.01056   0.00528  -0.0252   0.9923   0.5691
  -2.250  -0.1599   0.01045   0.00577  -0.0250   0.9851   0.7722
  -2.000  -0.1262   0.01054   0.00587  -0.0256   0.9768   0.8215
  -1.750  -0.0893   0.01067   0.00595  -0.0267   0.9703   0.8596
  -1.500  -0.0621   0.01064   0.00591  -0.0256   0.9601   0.8910
  -1.250  -0.0321   0.01060   0.00582  -0.0251   0.9511   0.9173
  -1.000   0.0069   0.01055   0.00570  -0.0266   0.9449   0.9386
  -0.750   0.0488   0.01050   0.00558  -0.0288   0.9377   0.9571
  -0.500   0.1047   0.01047   0.00546  -0.0341   0.9340   0.9701
  -0.250   0.1701   0.01038   0.00530  -0.0413   0.9323   0.9776
   0.000   0.2331   0.01021   0.00508  -0.0483   0.9299   0.9844
   0.250   0.2883   0.00996   0.00481  -0.0538   0.9210   0.9907
   0.500   0.3404   0.00968   0.00451  -0.0586   0.9108   0.9950
   0.750   0.3892   0.00938   0.00420  -0.0628   0.8961   0.9982
   1.000   0.4314   0.00914   0.00393  -0.0656   0.8768   1.0000
   1.250   0.4614   0.00899   0.00373  -0.0659   0.8523   1.0000
   1.500   0.4876   0.00892   0.00359  -0.0654   0.8264   1.0000
   1.750   0.5106   0.00890   0.00349  -0.0644   0.7995   1.0000
   2.000   0.5317   0.00894   0.00345  -0.0629   0.7724   1.0000
   2.250   0.5513   0.00901   0.00343  -0.0612   0.7454   1.0000
   2.500   0.5698   0.00913   0.00344  -0.0594   0.7187   1.0000
   2.750   0.5873   0.00926   0.00350  -0.0573   0.6921   1.0000
   3.000   0.6045   0.00942   0.00360  -0.0552   0.6658   1.0000
   3.250   0.6220   0.00960   0.00370  -0.0532   0.6394   1.0000
   3.500   0.6408   0.00981   0.00382  -0.0514   0.6121   1.0000
   3.750   0.6617   0.01004   0.00397  -0.0500   0.5838   1.0000
   4.000   0.6836   0.01029   0.00413  -0.0489   0.5542   1.0000
   4.250   0.7060   0.01057   0.00435  -0.0478   0.5233   1.0000
   4.500   0.7285   0.01088   0.00456  -0.0468   0.4913   1.0000
   4.750   0.7511   0.01120   0.00480  -0.0458   0.4566   1.0000
   5.000   0.7733   0.01158   0.00507  -0.0448   0.4213   1.0000
   5.250   0.7958   0.01197   0.00541  -0.0439   0.3855   1.0000
   5.500   0.8176   0.01243   0.00575  -0.0429   0.3451   1.0000
   5.750   0.8381   0.01299   0.00612  -0.0417   0.2956   1.0000
   6.000   0.8586   0.01363   0.00655  -0.0407   0.2439   1.0000
   6.250   0.8791   0.01434   0.00706  -0.0397   0.1977   1.0000
   6.500   0.8991   0.01515   0.00769  -0.0387   0.1509   1.0000
   6.750   0.9175   0.01620   0.00847  -0.0375   0.1022   1.0000
   7.000   0.9320   0.01782   0.00981  -0.0354   0.0590   1.0000
   7.250   0.9481   0.01921   0.01120  -0.0335   0.0470   1.0000
   7.500   0.9646   0.02053   0.01252  -0.0318   0.0410   1.0000
   7.750   0.9826   0.02183   0.01392  -0.0303   0.0373   1.0000
   8.000   1.0017   0.02313   0.01535  -0.0289   0.0347   1.0000
   8.250   1.0210   0.02457   0.01686  -0.0277   0.0327   1.0000
   8.500   1.0405   0.02646   0.01882  -0.0266   0.0311   1.0000
   8.750   1.0603   0.02980   0.02234  -0.0258   0.0293   1.0000
   9.000   1.0792   0.03102   0.02384  -0.0244   0.0279   1.0000
   9.250   1.0968   0.03346   0.02660  -0.0230   0.0270   1.0000
   9.500   1.1109   0.03632   0.02982  -0.0212   0.0265   1.0000
   9.750   1.1203   0.03958   0.03349  -0.0191   0.0263   1.0000
  10.000   1.1252   0.04270   0.03700  -0.0166   0.0257   1.0000
  10.250   1.1277   0.04541   0.04002  -0.0142   0.0248   1.0000
  10.500   1.1303   0.04766   0.04249  -0.0120   0.0237   1.0000
  10.750   1.1199   0.05091   0.04606  -0.0086   0.0237   1.0000
  11.000   1.0974   0.05502   0.05054  -0.0048   0.0243   1.0000
  11.250   1.0746   0.05928   0.05509  -0.0026   0.0248   1.0000
  11.500   1.0524   0.06375   0.05976  -0.0021   0.0249   1.0000
  11.750   1.0278   0.06919   0.06542  -0.0034   0.0254   1.0000
  12.000   1.0026   0.07562   0.07204  -0.0066   0.0258   1.0000
  12.250   0.9781   0.08300   0.07958  -0.0114   0.0261   1.0000
  12.500   0.9511   0.09230   0.08900  -0.0179   0.0273   1.0000
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