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RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG 8 AIRFOIL (rg8-il)
Reynolds number: 50,000
Max Cl/Cd: 37.8 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg8-il-50000-n5.txt
Download as CSV file: xf-rg8-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4860   0.09620   0.08895  -0.0426   1.0000   0.0499
  -9.750  -0.4891   0.09169   0.08450  -0.0438   1.0000   0.0496
  -9.500  -0.4947   0.08679   0.07967  -0.0456   1.0000   0.0492
  -9.250  -0.5045   0.08143   0.07438  -0.0479   1.0000   0.0489
  -9.000  -0.5184   0.07655   0.06956  -0.0499   1.0000   0.0485
  -8.750  -0.5384   0.07215   0.06522  -0.0511   1.0000   0.0481
  -8.500  -0.5552   0.06777   0.06084  -0.0521   1.0000   0.0478
  -8.250  -0.5689   0.06349   0.05647  -0.0525   1.0000   0.0475
  -8.000  -0.5790   0.05924   0.05205  -0.0526   1.0000   0.0474
  -7.750  -0.5845   0.05500   0.04754  -0.0523   1.0000   0.0474
  -7.500  -0.5845   0.05096   0.04318  -0.0520   1.0000   0.0475
  -7.250  -0.5798   0.04706   0.03886  -0.0515   1.0000   0.0478
  -7.000  -0.5705   0.04342   0.03473  -0.0509   1.0000   0.0483
  -6.750  -0.5570   0.04021   0.03101  -0.0502   1.0000   0.0491
  -6.500  -0.5413   0.03756   0.02804  -0.0495   1.0000   0.0510
  -6.250  -0.5241   0.03583   0.02616  -0.0487   1.0000   0.0543
  -6.000  -0.5051   0.03391   0.02395  -0.0478   1.0000   0.0576
  -5.750  -0.4844   0.03192   0.02158  -0.0468   1.0000   0.0605
  -5.500  -0.4638   0.03016   0.01960  -0.0455   1.0000   0.0635
  -5.250  -0.4440   0.02879   0.01820  -0.0443   1.0000   0.0678
  -5.000  -0.4232   0.02756   0.01675  -0.0430   1.0000   0.0758
  -4.750  -0.4029   0.02646   0.01557  -0.0421   1.0000   0.0882
  -4.500  -0.3824   0.02529   0.01450  -0.0414   1.0000   0.1065
  -4.250  -0.3610   0.02423   0.01357  -0.0410   1.0000   0.1411
  -4.000  -0.3391   0.02316   0.01271  -0.0408   1.0000   0.1882
  -3.750  -0.3164   0.02210   0.01192  -0.0409   1.0000   0.2466
  -3.500  -0.2938   0.02112   0.01138  -0.0408   1.0000   0.3302
  -3.250  -0.2747   0.02053   0.01139  -0.0394   1.0000   0.4404
  -3.000  -0.2567   0.02051   0.01156  -0.0373   1.0000   0.5345
  -2.750  -0.2387   0.02062   0.01166  -0.0352   1.0000   0.5953
  -2.500  -0.2217   0.02074   0.01175  -0.0329   1.0000   0.6404
  -2.250  -0.2056   0.02087   0.01183  -0.0304   1.0000   0.6781
  -2.000  -0.1832   0.02107   0.01195  -0.0292   0.9962   0.7144
  -1.750  -0.1526   0.02132   0.01212  -0.0294   0.9870   0.7495
  -1.500  -0.1227   0.02150   0.01221  -0.0295   0.9775   0.7821
  -1.250  -0.0927   0.02161   0.01222  -0.0296   0.9679   0.8132
  -1.000  -0.0620   0.02166   0.01221  -0.0298   0.9583   0.8434
  -0.750  -0.0328   0.02159   0.01210  -0.0299   0.9475   0.8731
  -0.500   0.0025   0.02153   0.01196  -0.0312   0.9373   0.9037
  -0.250   0.0504   0.02152   0.01186  -0.0353   0.9288   0.9344
   0.000   0.1032   0.02148   0.01173  -0.0408   0.9191   0.9678
   0.250   0.1459   0.02141   0.01154  -0.0447   0.9070   1.0000
   0.500   0.1823   0.02143   0.01145  -0.0473   0.8949   1.0000
   0.750   0.2202   0.02146   0.01137  -0.0499   0.8831   1.0000
   1.000   0.2604   0.02146   0.01129  -0.0527   0.8720   1.0000
   1.250   0.3002   0.02143   0.01120  -0.0553   0.8606   1.0000
   1.500   0.3363   0.02141   0.01115  -0.0570   0.8475   1.0000
   2.000   0.4095   0.02135   0.01107  -0.0603   0.8207   1.0000
   2.250   0.4454   0.02130   0.01104  -0.0617   0.8065   1.0000
   2.500   0.4810   0.02124   0.01100  -0.0629   0.7918   1.0000
   2.750   0.5166   0.02117   0.01096  -0.0639   0.7764   1.0000
   3.000   0.5521   0.02108   0.01093  -0.0649   0.7604   1.0000
   3.250   0.5847   0.02107   0.01096  -0.0653   0.7423   1.0000
   3.500   0.6157   0.02110   0.01103  -0.0655   0.7226   1.0000
   3.750   0.6494   0.02107   0.01108  -0.0659   0.7031   1.0000
   4.000   0.6788   0.02117   0.01122  -0.0657   0.6811   1.0000
   4.250   0.7101   0.02124   0.01131  -0.0658   0.6591   1.0000
   4.500   0.7373   0.02143   0.01155  -0.0652   0.6346   1.0000
   4.750   0.7651   0.02164   0.01182  -0.0647   0.6098   1.0000
   5.000   0.7925   0.02188   0.01207  -0.0641   0.5842   1.0000
   5.250   0.8178   0.02219   0.01240  -0.0633   0.5573   1.0000
   5.500   0.8418   0.02258   0.01281  -0.0623   0.5295   1.0000
   5.750   0.8650   0.02301   0.01330  -0.0612   0.5011   1.0000
   6.000   0.8873   0.02350   0.01379  -0.0599   0.4722   1.0000
   6.250   0.9086   0.02404   0.01433  -0.0586   0.4430   1.0000
   6.500   0.9289   0.02464   0.01493  -0.0572   0.4133   1.0000
   6.750   0.9480   0.02531   0.01558  -0.0556   0.3834   1.0000
   7.000   0.9661   0.02605   0.01635  -0.0540   0.3533   1.0000
   7.250   0.9830   0.02687   0.01717  -0.0523   0.3232   1.0000
   7.500   0.9989   0.02777   0.01807  -0.0506   0.2935   1.0000
   7.750   1.0137   0.02876   0.01904  -0.0487   0.2645   1.0000
   8.000   1.0276   0.02986   0.02011  -0.0468   0.2370   1.0000
   8.250   1.0399   0.03106   0.02126  -0.0449   0.2110   1.0000
   8.500   1.0521   0.03237   0.02261  -0.0430   0.1860   1.0000
   8.750   1.0631   0.03382   0.02410  -0.0410   0.1639   1.0000
   9.000   1.0723   0.03534   0.02562  -0.0389   0.1447   1.0000
   9.250   1.0800   0.03699   0.02723  -0.0367   0.1284   1.0000
   9.500   1.0880   0.03879   0.02905  -0.0346   0.1135   1.0000
   9.750   1.0945   0.04070   0.03101  -0.0325   0.1000   1.0000
  10.000   1.0995   0.04272   0.03307  -0.0305   0.0886   1.0000
  10.250   1.1040   0.04487   0.03538  -0.0286   0.0777   1.0000
  10.500   1.1078   0.04723   0.03791  -0.0268   0.0687   1.0000
  10.750   1.1088   0.04967   0.04032  -0.0253   0.0622   1.0000
  11.000   1.1116   0.05234   0.04330  -0.0239   0.0558   1.0000
  11.250   1.1121   0.05500   0.04596  -0.0228   0.0518   1.0000
  11.500   1.1154   0.05836   0.04973  -0.0217   0.0481   1.0000
  11.750   1.1147   0.06174   0.05338  -0.0210   0.0453   1.0000
  12.000   1.1116   0.06508   0.05686  -0.0206   0.0431   1.0000
  12.250   1.1100   0.06845   0.06025  -0.0205   0.0412   1.0000
  12.500   1.1007   0.07311   0.06523  -0.0211   0.0400   1.0000
  12.750   1.0880   0.07838   0.07084  -0.0224   0.0393   1.0000
  13.000   1.0728   0.08429   0.07704  -0.0246   0.0388   1.0000
  13.250   1.0555   0.09092   0.08393  -0.0277   0.0387   1.0000
  13.500   1.0361   0.09845   0.09168  -0.0318   0.0388   1.0000
  13.750   1.0160   0.10674   0.10017  -0.0367   0.0392   1.0000
  14.000   0.9947   0.11605   0.10964  -0.0424   0.0396   1.0000
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