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RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG 8 AIRFOIL (rg8-il)
Reynolds number: 100,000
Max Cl/Cd: 53.74 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg8-il-100000-n5.txt
Download as CSV file: xf-rg8-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 8 AIRFOIL                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4916   0.09194   0.08677  -0.0401   1.0000   0.0281
 -10.000  -0.4999   0.08636   0.08126  -0.0422   1.0000   0.0279
  -9.750  -0.5114   0.08002   0.07499  -0.0450   1.0000   0.0276
  -9.500  -0.5307   0.07161   0.06662  -0.0499   1.0000   0.0271
  -9.250  -0.5575   0.06467   0.05969  -0.0541   1.0000   0.0268
  -9.000  -0.5855   0.06041   0.05541  -0.0548   1.0000   0.0265
  -8.750  -0.6080   0.05592   0.05079  -0.0551   1.0000   0.0263
  -8.500  -0.6228   0.05171   0.04636  -0.0546   1.0000   0.0262
  -8.250  -0.6313   0.04753   0.04188  -0.0538   1.0000   0.0262
  -8.000  -0.6333   0.04354   0.03751  -0.0528   1.0000   0.0263
  -7.750  -0.6293   0.03985   0.03338  -0.0519   1.0000   0.0265
  -7.500  -0.6199   0.03664   0.02973  -0.0510   1.0000   0.0268
  -7.250  -0.6064   0.03398   0.02660  -0.0501   1.0000   0.0278
  -7.000  -0.5898   0.03191   0.02405  -0.0492   1.0000   0.0290
  -6.750  -0.5729   0.02969   0.02167  -0.0485   1.0000   0.0301
  -6.500  -0.5539   0.02799   0.01977  -0.0476   1.0000   0.0309
  -6.250  -0.5338   0.02648   0.01807  -0.0468   1.0000   0.0318
  -6.000  -0.5131   0.02515   0.01655  -0.0459   1.0000   0.0329
  -5.750  -0.4919   0.02395   0.01519  -0.0451   1.0000   0.0342
  -5.500  -0.4702   0.02287   0.01397  -0.0443   1.0000   0.0359
  -5.250  -0.4483   0.02196   0.01290  -0.0435   1.0000   0.0379
  -5.000  -0.4214   0.02102   0.01195  -0.0441   0.9984   0.0421
  -4.750  -0.3861   0.02030   0.01107  -0.0460   0.9944   0.0490
  -4.500  -0.3522   0.01936   0.01013  -0.0478   0.9900   0.0598
  -4.250  -0.3172   0.01856   0.00942  -0.0498   0.9856   0.0860
  -4.000  -0.2826   0.01794   0.00899  -0.0518   0.9810   0.1306
  -3.750  -0.2496   0.01722   0.00864  -0.0538   0.9755   0.2011
  -3.500  -0.2135   0.01659   0.00827  -0.0561   0.9711   0.2753
  -3.250  -0.1829   0.01595   0.00800  -0.0572   0.9645   0.3654
  -3.000  -0.1489   0.01558   0.00806  -0.0586   0.9591   0.4781
  -2.750  -0.1185   0.01549   0.00805  -0.0590   0.9515   0.5451
  -2.500  -0.0829   0.01546   0.00799  -0.0603   0.9457   0.5884
  -2.250  -0.0530   0.01542   0.00791  -0.0606   0.9373   0.6197
  -2.000  -0.0169   0.01537   0.00783  -0.0619   0.9316   0.6474
  -1.750   0.0123   0.01531   0.00772  -0.0619   0.9225   0.6702
  -1.500   0.0489   0.01521   0.00760  -0.0633   0.9170   0.6919
  -1.000   0.1112   0.01500   0.00734  -0.0639   0.9003   0.7289
  -0.750   0.1424   0.01487   0.00721  -0.0641   0.8916   0.7460
  -0.500   0.1735   0.01473   0.00706  -0.0644   0.8825   0.7620
  -0.250   0.2095   0.01455   0.00688  -0.0656   0.8752   0.7771
   0.000   0.2393   0.01443   0.00675  -0.0656   0.8642   0.7912
   0.250   0.2711   0.01427   0.00660  -0.0660   0.8537   0.8044
   0.500   0.3057   0.01408   0.00641  -0.0669   0.8439   0.8170
   0.750   0.3379   0.01392   0.00625  -0.0674   0.8321   0.8299
   1.000   0.3686   0.01378   0.00613  -0.0676   0.8187   0.8433
   1.250   0.3993   0.01364   0.00601  -0.0677   0.8047   0.8576
   1.500   0.4302   0.01351   0.00589  -0.0679   0.7898   0.8730
   1.750   0.4616   0.01338   0.00578  -0.0681   0.7740   0.8908
   2.000   0.4929   0.01329   0.00572  -0.0684   0.7561   0.9124
   2.250   0.5289   0.01322   0.00566  -0.0698   0.7369   0.9380
   2.500   0.5707   0.01318   0.00561  -0.0724   0.7165   0.9740
   2.750   0.6026   0.01325   0.00563  -0.0733   0.6943   1.0000
   3.250   0.6601   0.01356   0.00579  -0.0737   0.6488   1.0000
   3.500   0.6875   0.01376   0.00594  -0.0735   0.6248   1.0000
   3.750   0.7143   0.01399   0.00609  -0.0732   0.6003   1.0000
   4.000   0.7398   0.01425   0.00629  -0.0728   0.5747   1.0000
   4.250   0.7650   0.01454   0.00651  -0.0722   0.5487   1.0000
   4.500   0.7896   0.01486   0.00679  -0.0715   0.5224   1.0000
   4.750   0.8136   0.01521   0.00707  -0.0708   0.4956   1.0000
   5.000   0.8370   0.01559   0.00738  -0.0699   0.4685   1.0000
   5.250   0.8599   0.01600   0.00772  -0.0690   0.4408   1.0000
   5.500   0.8823   0.01644   0.00813  -0.0680   0.4127   1.0000
   5.750   0.9041   0.01691   0.00855  -0.0670   0.3842   1.0000
   6.000   0.9255   0.01742   0.00900  -0.0659   0.3556   1.0000
   6.250   0.9465   0.01796   0.00949  -0.0648   0.3270   1.0000
   6.500   0.9669   0.01855   0.01002  -0.0636   0.2983   1.0000
   6.750   0.9867   0.01918   0.01062  -0.0624   0.2696   1.0000
   7.000   1.0060   0.01986   0.01125  -0.0611   0.2410   1.0000
   7.250   1.0249   0.02060   0.01193  -0.0598   0.2135   1.0000
   7.500   1.0432   0.02138   0.01267  -0.0585   0.1869   1.0000
   7.750   1.0609   0.02223   0.01348  -0.0571   0.1624   1.0000
   8.000   1.0775   0.02317   0.01436  -0.0556   0.1404   1.0000
   8.250   1.0941   0.02412   0.01536  -0.0540   0.1205   1.0000
   8.500   1.1086   0.02521   0.01640  -0.0523   0.1024   1.0000
   8.750   1.1229   0.02632   0.01749  -0.0506   0.0844   1.0000
   9.000   1.1360   0.02748   0.01860  -0.0488   0.0671   1.0000
   9.250   1.1469   0.02871   0.01981  -0.0467   0.0538   1.0000
   9.500   1.1563   0.03003   0.02117  -0.0444   0.0441   1.0000
   9.750   1.1633   0.03153   0.02272  -0.0418   0.0369   1.0000
  10.000   1.1683   0.03317   0.02444  -0.0392   0.0323   1.0000
  10.250   1.1709   0.03503   0.02646  -0.0364   0.0292   1.0000
  10.500   1.1749   0.03686   0.02847  -0.0339   0.0268   1.0000
  10.750   1.1781   0.03874   0.03047  -0.0318   0.0247   1.0000
  11.000   1.1784   0.04092   0.03274  -0.0297   0.0232   1.0000
  11.250   1.1801   0.04319   0.03516  -0.0279   0.0219   1.0000
  11.500   1.1833   0.04542   0.03761  -0.0265   0.0204   1.0000
  11.750   1.1848   0.04787   0.04024  -0.0252   0.0195   1.0000
  12.000   1.1849   0.05054   0.04308  -0.0242   0.0187   1.0000
  12.250   1.1839   0.05344   0.04615  -0.0235   0.0181   1.0000
  12.500   1.1818   0.05659   0.04945  -0.0231   0.0177   1.0000
  12.750   1.1786   0.06000   0.05302  -0.0230   0.0173   1.0000
  13.000   1.1740   0.06377   0.05694  -0.0233   0.0170   1.0000
  13.250   1.1682   0.06790   0.06124  -0.0238   0.0168   1.0000
  13.500   1.1605   0.07250   0.06606  -0.0249   0.0166   1.0000
  13.750   1.1511   0.07752   0.07133  -0.0265   0.0165   1.0000
  14.000   1.1390   0.08321   0.07726  -0.0288   0.0164   1.0000
  14.250   1.1257   0.08936   0.08365  -0.0318   0.0164   1.0000
  14.500   1.1109   0.09613   0.09064  -0.0354   0.0164   1.0000
  14.750   1.0949   0.10357   0.09829  -0.0397   0.0164   1.0000
  15.000   1.0778   0.11169   0.10661  -0.0447   0.0164   1.0000
  15.250   1.0602   0.12046   0.11554  -0.0503   0.0165   1.0000
  15.500   1.0425   0.12975   0.12498  -0.0563   0.0166   1.0000
  15.750   0.9708   0.15862   0.15422  -0.0742   0.0182   1.0000
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