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RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RG 8 AIRFOIL (rg8-il)
Reynolds number: 500,000
Max Cl/Cd: 83.34 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg8-il-500000-n5.txt
Download as CSV file: xf-rg8-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7381   0.05348   0.05076  -0.0601   1.0000   0.0082
 -11.500  -0.7685   0.04622   0.04331  -0.0647   1.0000   0.0082
 -11.250  -0.7862   0.04238   0.03935  -0.0657   1.0000   0.0082
 -11.000  -0.8199   0.03900   0.03582  -0.0635   1.0000   0.0081
 -10.750  -0.8302   0.03683   0.03351  -0.0614   1.0000   0.0082
 -10.500  -0.8344   0.03462   0.03113  -0.0594   1.0000   0.0083
 -10.250  -0.8218   0.03277   0.02910  -0.0597   0.9990   0.0086
 -10.000  -0.8001   0.03046   0.02654  -0.0619   0.9967   0.0089
  -9.750  -0.7769   0.02808   0.02388  -0.0639   0.9947   0.0091
  -9.500  -0.7538   0.02607   0.02160  -0.0651   0.9925   0.0094
  -9.250  -0.7295   0.02434   0.01962  -0.0661   0.9900   0.0097
  -9.000  -0.7029   0.02284   0.01789  -0.0672   0.9877   0.0100
  -8.750  -0.6745   0.02155   0.01639  -0.0685   0.9858   0.0103
  -8.500  -0.6447   0.02039   0.01505  -0.0698   0.9843   0.0105
  -8.250  -0.6129   0.01968   0.01420  -0.0713   0.9831   0.0108
  -8.000  -0.5920   0.01807   0.01243  -0.0709   0.9790   0.0113
  -7.750  -0.5646   0.01696   0.01120  -0.0716   0.9762   0.0118
  -7.500  -0.5347   0.01613   0.01029  -0.0726   0.9740   0.0121
  -7.250  -0.5034   0.01539   0.00947  -0.0738   0.9723   0.0125
  -7.000  -0.4711   0.01470   0.00871  -0.0752   0.9709   0.0130
  -6.750  -0.4477   0.01412   0.00806  -0.0746   0.9657   0.0133
  -6.500  -0.4178   0.01352   0.00738  -0.0753   0.9626   0.0138
  -6.250  -0.3858   0.01296   0.00675  -0.0764   0.9603   0.0142
  -6.000  -0.3526   0.01247   0.00620  -0.0778   0.9585   0.0148
  -5.750  -0.3271   0.01209   0.00576  -0.0774   0.9531   0.0153
  -5.500  -0.2971   0.01155   0.00516  -0.0781   0.9494   0.0163
  -5.250  -0.2648   0.01109   0.00464  -0.0792   0.9467   0.0175
  -5.000  -0.2311   0.01070   0.00422  -0.0805   0.9447   0.0189
  -4.750  -0.2055   0.01040   0.00389  -0.0800   0.9377   0.0206
  -4.500  -0.1725   0.01003   0.00354  -0.0812   0.9340   0.0266
  -4.250  -0.1364   0.00960   0.00319  -0.0831   0.9313   0.0489
  -4.000  -0.1066   0.00926   0.00294  -0.0837   0.9243   0.0702
  -3.750  -0.0709   0.00886   0.00267  -0.0856   0.9194   0.1050
  -3.500  -0.0368   0.00855   0.00245  -0.0871   0.9130   0.1338
  -3.250  -0.0020   0.00822   0.00223  -0.0887   0.9053   0.1730
  -3.000   0.0315   0.00793   0.00204  -0.0901   0.8960   0.2104
  -2.750   0.0650   0.00755   0.00184  -0.0915   0.8855   0.2744
  -2.500   0.0964   0.00710   0.00166  -0.0926   0.8730   0.3630
  -2.250   0.1262   0.00676   0.00156  -0.0932   0.8590   0.4508
  -2.000   0.1554   0.00664   0.00152  -0.0934   0.8438   0.5008
  -1.750   0.1840   0.00662   0.00148  -0.0934   0.8278   0.5261
  -1.500   0.2120   0.00663   0.00144  -0.0933   0.8107   0.5450
  -1.250   0.2395   0.00666   0.00142  -0.0931   0.7928   0.5620
  -1.000   0.2666   0.00670   0.00140  -0.0928   0.7746   0.5767
  -0.750   0.2934   0.00676   0.00140  -0.0925   0.7556   0.5899
  -0.500   0.3199   0.00682   0.00141  -0.0921   0.7359   0.6013
   0.000   0.3725   0.00699   0.00144  -0.0912   0.6960   0.6230
   0.250   0.3984   0.00708   0.00147  -0.0907   0.6753   0.6340
   0.500   0.4244   0.00718   0.00152  -0.0902   0.6548   0.6441
   0.750   0.4503   0.00729   0.00156  -0.0898   0.6336   0.6544
   1.000   0.4760   0.00741   0.00162  -0.0892   0.6122   0.6649
   1.250   0.5018   0.00753   0.00170  -0.0887   0.5903   0.6743
   1.750   0.5531   0.00780   0.00185  -0.0878   0.5462   0.6907
   2.000   0.5788   0.00796   0.00194  -0.0873   0.5239   0.6988
   2.250   0.6042   0.00812   0.00205  -0.0868   0.5007   0.7071
   2.500   0.6297   0.00829   0.00216  -0.0863   0.4777   0.7154
   2.750   0.6550   0.00848   0.00229  -0.0858   0.4548   0.7250
   3.000   0.6804   0.00865   0.00243  -0.0853   0.4317   0.7347
   3.250   0.7055   0.00885   0.00259  -0.0847   0.4088   0.7447
   3.500   0.7306   0.00906   0.00275  -0.0842   0.3855   0.7561
   3.750   0.7554   0.00927   0.00292  -0.0836   0.3619   0.7687
   4.000   0.7798   0.00951   0.00312  -0.0830   0.3378   0.7819
   4.250   0.8042   0.00974   0.00333  -0.0823   0.3143   0.7961
   4.500   0.8283   0.00998   0.00355  -0.0816   0.2920   0.8125
   4.750   0.8516   0.01024   0.00378  -0.0808   0.2691   0.8314
   5.000   0.8742   0.01049   0.00402  -0.0797   0.2449   0.8537
   5.250   0.8951   0.01077   0.00429  -0.0783   0.2202   0.8815
   5.500   0.9137   0.01102   0.00453  -0.0764   0.1966   0.9263
   5.750   0.9411   0.01134   0.00479  -0.0765   0.1732   1.0000
   6.000   0.9647   0.01178   0.00512  -0.0759   0.1495   1.0000
   6.250   0.9875   0.01227   0.00549  -0.0751   0.1244   1.0000
   6.500   1.0099   0.01280   0.00590  -0.0744   0.1010   1.0000
   6.750   1.0328   0.01327   0.00629  -0.0736   0.0831   1.0000
   7.000   1.0551   0.01377   0.00672  -0.0728   0.0671   1.0000
   7.250   1.0766   0.01434   0.00719  -0.0719   0.0511   1.0000
   7.500   1.0985   0.01487   0.00766  -0.0710   0.0397   1.0000
   7.750   1.1200   0.01540   0.00817  -0.0701   0.0308   1.0000
   8.000   1.1412   0.01595   0.00870  -0.0691   0.0232   1.0000
   8.250   1.1614   0.01657   0.00929  -0.0679   0.0156   1.0000
   8.500   1.1810   0.01722   0.00994  -0.0667   0.0109   1.0000
   8.750   1.2004   0.01786   0.01061  -0.0654   0.0089   1.0000
   9.000   1.2198   0.01848   0.01128  -0.0641   0.0079   1.0000
   9.250   1.2387   0.01909   0.01196  -0.0627   0.0072   1.0000
   9.500   1.2566   0.01975   0.01270  -0.0612   0.0066   1.0000
   9.750   1.2723   0.02046   0.01349  -0.0594   0.0061   1.0000
  10.000   1.2854   0.02129   0.01440  -0.0571   0.0057   1.0000
  10.250   1.2967   0.02223   0.01544  -0.0546   0.0055   1.0000
  10.500   1.3098   0.02301   0.01631  -0.0524   0.0054   1.0000
  10.750   1.3213   0.02389   0.01729  -0.0502   0.0052   1.0000
  11.000   1.3317   0.02485   0.01835  -0.0478   0.0051   1.0000
  11.250   1.3408   0.02589   0.01949  -0.0454   0.0050   1.0000
  11.500   1.3487   0.02703   0.02076  -0.0430   0.0048   1.0000
  11.750   1.3555   0.02826   0.02210  -0.0407   0.0047   1.0000
  12.000   1.3608   0.02964   0.02360  -0.0384   0.0046   1.0000
  12.250   1.3649   0.03117   0.02525  -0.0362   0.0045   1.0000
  12.500   1.3679   0.03286   0.02705  -0.0341   0.0044   1.0000
  12.750   1.3698   0.03471   0.02903  -0.0323   0.0043   1.0000
  13.000   1.3703   0.03681   0.03125  -0.0307   0.0042   1.0000
  13.250   1.3697   0.03913   0.03370  -0.0294   0.0042   1.0000
  13.500   1.3683   0.04169   0.03639  -0.0284   0.0041   1.0000
  13.750   1.3664   0.04447   0.03930  -0.0278   0.0040   1.0000
  14.000   1.3621   0.04771   0.04268  -0.0276   0.0040   1.0000
  14.250   1.3573   0.05121   0.04631  -0.0278   0.0039   1.0000
  14.500   1.3523   0.05497   0.05020  -0.0285   0.0039   1.0000
  14.750   1.3448   0.05930   0.05468  -0.0296   0.0038   1.0000
  15.000   1.3363   0.06404   0.05956  -0.0312   0.0038   1.0000
  15.250   1.3257   0.06938   0.06508  -0.0333   0.0038   1.0000
  15.500   1.3163   0.07482   0.07066  -0.0357   0.0037   1.0000
  15.750   1.3032   0.08115   0.07713  -0.0387   0.0037   1.0000
  16.000   1.2908   0.08761   0.08374  -0.0420   0.0037   1.0000
  16.250   1.2776   0.09448   0.09076  -0.0456   0.0037   1.0000
  16.500   1.2630   0.10184   0.09826  -0.0496   0.0036   1.0000
  16.750   1.2493   0.10924   0.10580  -0.0536   0.0037   1.0000
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