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RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG 14 AIRFOIL (rg14-il)
Reynolds number: 100,000
Max Cl/Cd: 49.18 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg14-il-100000.txt
Download as CSV file: xf-rg14-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4867   0.10303   0.09801  -0.0162   1.0000   0.0917
  -9.000  -0.4925   0.09970   0.09476  -0.0191   1.0000   0.0956
  -8.750  -0.5165   0.09663   0.09183  -0.0261   1.0000   0.0973
  -8.500  -0.5031   0.09172   0.08694  -0.0236   1.0000   0.0995
  -8.250  -0.4912   0.08857   0.08379  -0.0217   1.0000   0.1029
  -8.000  -0.4950   0.08524   0.08053  -0.0231   1.0000   0.1067
  -7.750  -0.5189   0.08140   0.07678  -0.0292   1.0000   0.1100
  -7.500  -0.5332   0.07669   0.07205  -0.0330   1.0000   0.1120
  -7.250  -0.5141   0.07366   0.06912  -0.0285   1.0000   0.1156
  -7.000  -0.5148   0.07020   0.06565  -0.0296   1.0000   0.1211
  -6.750  -0.5220   0.06580   0.06117  -0.0318   1.0000   0.1269
  -6.500  -0.5121   0.06283   0.05824  -0.0301   1.0000   0.1315
  -6.250  -0.5136   0.05891   0.05417  -0.0312   1.0000   0.1409
  -6.000  -0.5035   0.05596   0.05122  -0.0298   1.0000   0.1467
  -5.750  -0.4977   0.04242   0.03630  -0.0330   1.0000   0.0728
  -5.500  -0.4820   0.03678   0.03001  -0.0309   1.0000   0.0560
  -5.250  -0.4666   0.03344   0.02628  -0.0294   1.0000   0.0554
  -5.000  -0.4488   0.03074   0.02307  -0.0277   1.0000   0.0564
  -4.750  -0.4292   0.02810   0.01993  -0.0260   1.0000   0.0569
  -4.500  -0.4080   0.02553   0.01696  -0.0245   1.0000   0.0567
  -4.250  -0.3853   0.02353   0.01454  -0.0230   1.0000   0.0577
  -4.000  -0.3627   0.02111   0.01205  -0.0219   1.0000   0.0611
  -3.750  -0.3399   0.01974   0.01055  -0.0205   1.0000   0.0692
  -3.500  -0.3185   0.01833   0.00918  -0.0193   1.0000   0.0879
  -3.250  -0.2974   0.01713   0.00813  -0.0181   1.0000   0.1225
  -3.000  -0.2767   0.01585   0.00718  -0.0168   1.0000   0.1793
  -2.750  -0.2584   0.01410   0.00650  -0.0156   1.0000   0.3371
  -2.500  -0.2500   0.01248   0.00662  -0.0108   1.0000   0.6931
  -2.250  -0.2360   0.01250   0.00699  -0.0053   1.0000   0.9002
  -2.000  -0.1056   0.01281   0.00660  -0.0236   1.0000   1.0000
  -1.750  -0.1048   0.01273   0.00640  -0.0196   1.0000   1.0000
  -1.500  -0.1013   0.01271   0.00625  -0.0161   1.0000   1.0000
  -1.250  -0.0939   0.01275   0.00616  -0.0133   1.0000   1.0000
  -1.000  -0.0824   0.01287   0.00614  -0.0112   1.0000   1.0000
  -0.750  -0.0683   0.01305   0.00618  -0.0097   1.0000   1.0000
  -0.500  -0.0529   0.01329   0.00627  -0.0084   1.0000   1.0000
  -0.250  -0.0234   0.01366   0.00652  -0.0099   0.9961   1.0000
   0.000   0.0297   0.01414   0.00687  -0.0157   0.9846   1.0000
   0.250   0.0809   0.01449   0.00712  -0.0209   0.9724   1.0000
   0.500   0.1317   0.01473   0.00730  -0.0259   0.9596   1.0000
   0.750   0.1820   0.01486   0.00741  -0.0306   0.9463   1.0000
   1.000   0.2322   0.01489   0.00743  -0.0351   0.9329   1.0000
   1.250   0.2835   0.01481   0.00738  -0.0396   0.9196   1.0000
   1.500   0.3371   0.01460   0.00724  -0.0443   0.9065   1.0000
   1.750   0.3867   0.01431   0.00702  -0.0480   0.8918   1.0000
   2.000   0.4331   0.01398   0.00675  -0.0508   0.8757   1.0000
   2.250   0.4695   0.01374   0.00657  -0.0516   0.8551   1.0000
   2.500   0.5047   0.01350   0.00640  -0.0520   0.8338   1.0000
   2.750   0.5323   0.01339   0.00631  -0.0510   0.8083   1.0000
   3.000   0.5583   0.01335   0.00627  -0.0498   0.7815   1.0000
   3.250   0.5829   0.01336   0.00626  -0.0482   0.7531   1.0000
   3.500   0.6068   0.01343   0.00633  -0.0466   0.7234   1.0000
   3.750   0.6291   0.01357   0.00643  -0.0448   0.6912   1.0000
   4.000   0.6512   0.01375   0.00656  -0.0430   0.6576   1.0000
   4.250   0.6731   0.01398   0.00671  -0.0412   0.6227   1.0000
   4.500   0.6945   0.01426   0.00691  -0.0395   0.5858   1.0000
   4.750   0.7154   0.01458   0.00722  -0.0377   0.5467   1.0000
   5.000   0.7358   0.01496   0.00750  -0.0359   0.5056   1.0000
   5.250   0.7558   0.01540   0.00783  -0.0341   0.4627   1.0000
   5.500   0.7751   0.01592   0.00821  -0.0323   0.4175   1.0000
   5.750   0.7937   0.01652   0.00868  -0.0305   0.3684   1.0000
   6.000   0.8116   0.01726   0.00923  -0.0286   0.3179   1.0000
   6.250   0.8287   0.01817   0.00990  -0.0268   0.2678   1.0000
   6.500   0.8455   0.01923   0.01082  -0.0250   0.2183   1.0000
   6.750   0.8620   0.02047   0.01184  -0.0233   0.1756   1.0000
   7.000   0.8785   0.02186   0.01306  -0.0216   0.1390   1.0000
   7.250   0.8951   0.02334   0.01440  -0.0200   0.1093   1.0000
   7.500   0.9133   0.02535   0.01635  -0.0183   0.0882   1.0000
   7.750   0.9310   0.02700   0.01799  -0.0169   0.0709   1.0000
   8.000   0.9521   0.02951   0.02063  -0.0156   0.0604   1.0000
   8.250   0.9705   0.03182   0.02306  -0.0143   0.0514   1.0000
   8.500   0.9897   0.03410   0.02555  -0.0130   0.0460   1.0000
   8.750   1.0075   0.03882   0.03048  -0.0121   0.0433   1.0000
   9.000   1.0191   0.04196   0.03420  -0.0099   0.0426   1.0000
   9.250   1.0256   0.04541   0.03823  -0.0074   0.0417   1.0000
   9.500   1.0282   0.04916   0.04247  -0.0050   0.0413   1.0000
   9.750   1.0246   0.05273   0.04652  -0.0023   0.0402   1.0000
  10.000   1.0169   0.05665   0.05081   0.0001   0.0401   1.0000
  10.250   1.0037   0.06046   0.05494   0.0025   0.0401   1.0000
  10.500   0.9862   0.06412   0.05882   0.0049   0.0405   1.0000
  10.750   0.9671   0.06820   0.06307   0.0059   0.0410   1.0000
  11.000   0.9454   0.07284   0.06788   0.0053   0.0412   1.0000
  11.250   0.9272   0.07821   0.07336   0.0033   0.0420   1.0000
  11.500   0.9060   0.08444   0.07970  -0.0004   0.0423   1.0000
  11.750   0.8958   0.09090   0.08617  -0.0029   0.0432   1.0000
  12.000   0.7272   0.10750   0.10321  -0.0153   0.0532   1.0000
  12.250   0.7193   0.11376   0.10946  -0.0174   0.0543   1.0000
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