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RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RG 14 AIRFOIL (rg14-il)
Reynolds number: 50,000
Max Cl/Cd: 33.25 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg14-il-50000.txt
Download as CSV file: xf-rg14-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4845   0.09641   0.08978  -0.0067   1.0000   0.2776
  -7.750  -0.4864   0.09353   0.08699  -0.0062   1.0000   0.2911
  -7.500  -0.4871   0.09060   0.08414  -0.0054   1.0000   0.3048
  -7.000  -0.4662   0.08309   0.07670  -0.0024   1.0000   0.3368
  -6.750  -0.4710   0.08070   0.07442  -0.0004   1.0000   0.3574
  -6.500  -0.4626   0.07756   0.07133   0.0022   1.0000   0.3839
  -5.750  -0.4969   0.05056   0.04308  -0.0328   1.0000   0.1227
  -5.500  -0.4838   0.04551   0.03730  -0.0325   1.0000   0.1105
  -5.250  -0.4675   0.04161   0.03321  -0.0315   1.0000   0.1075
  -5.000  -0.4500   0.03806   0.02918  -0.0304   1.0000   0.1063
  -4.750  -0.4308   0.03508   0.02553  -0.0291   1.0000   0.1097
  -4.500  -0.4106   0.03232   0.02258  -0.0280   1.0000   0.1155
  -4.250  -0.3875   0.02972   0.01954  -0.0266   1.0000   0.1203
  -4.000  -0.3645   0.02747   0.01703  -0.0253   1.0000   0.1337
  -3.750  -0.3408   0.02534   0.01465  -0.0240   1.0000   0.1552
  -3.500  -0.3176   0.02354   0.01286  -0.0225   1.0000   0.1927
  -3.250  -0.2933   0.02159   0.01124  -0.0212   1.0000   0.2512
  -3.000  -0.1271   0.01786   0.00980  -0.0354   1.0000   1.0000
  -2.750  -0.1232   0.01744   0.00914  -0.0327   1.0000   1.0000
  -2.500  -0.1175   0.01716   0.00857  -0.0299   1.0000   1.0000
  -2.250  -0.1110   0.01696   0.00815  -0.0269   1.0000   1.0000
  -2.000  -0.1040   0.01683   0.00781  -0.0240   1.0000   1.0000
  -1.750  -0.0960   0.01675   0.00753  -0.0211   1.0000   1.0000
  -1.500  -0.0871   0.01672   0.00731  -0.0184   1.0000   1.0000
  -1.250  -0.0765   0.01674   0.00714  -0.0161   1.0000   1.0000
  -1.000  -0.0641   0.01682   0.00703  -0.0140   1.0000   1.0000
  -0.750  -0.0502   0.01694   0.00698  -0.0123   1.0000   1.0000
  -0.500  -0.0352   0.01710   0.00696  -0.0108   1.0000   1.0000
  -0.250  -0.0196   0.01732   0.00703  -0.0095   1.0000   1.0000
   0.000  -0.0036   0.01758   0.00717  -0.0083   1.0000   1.0000
   0.250   0.0127   0.01790   0.00738  -0.0073   1.0000   1.0000
   0.500   0.0291   0.01826   0.00765  -0.0064   1.0000   1.0000
   0.750   0.0454   0.01868   0.00798  -0.0057   1.0000   1.0000
   1.000   0.0616   0.01916   0.00839  -0.0050   1.0000   1.0000
   1.250   0.0776   0.01970   0.00889  -0.0045   1.0000   1.0000
   1.500   0.0934   0.02032   0.00947  -0.0041   1.0000   1.0000
   1.750   0.1088   0.02100   0.01013  -0.0038   1.0000   1.0000
   2.000   0.1471   0.02209   0.01123  -0.0080   0.9892   1.0000
   2.250   0.2102   0.02339   0.01261  -0.0164   0.9657   1.0000
   2.500   0.2729   0.02442   0.01377  -0.0241   0.9420   1.0000
   2.750   0.3303   0.02510   0.01460  -0.0303   0.9164   1.0000
   3.000   0.3855   0.02554   0.01523  -0.0356   0.8901   1.0000
   3.250   0.4425   0.02571   0.01567  -0.0405   0.8632   1.0000
   3.500   0.5034   0.02550   0.01575  -0.0453   0.8359   1.0000
   3.750   0.5591   0.02501   0.01555  -0.0483   0.8075   1.0000
   4.000   0.6100   0.02432   0.01519  -0.0497   0.7777   1.0000
   4.250   0.6437   0.02402   0.01508  -0.0485   0.7436   1.0000
   4.500   0.6813   0.02342   0.01463  -0.0471   0.7089   1.0000
   4.750   0.7081   0.02326   0.01456  -0.0446   0.6697   1.0000
   5.000   0.7338   0.02317   0.01457  -0.0418   0.6280   1.0000
   5.250   0.7578   0.02322   0.01459  -0.0389   0.5834   1.0000
   5.500   0.7780   0.02355   0.01486  -0.0359   0.5344   1.0000
   5.750   0.7980   0.02400   0.01518  -0.0329   0.4829   1.0000
   6.000   0.8165   0.02468   0.01565  -0.0300   0.4288   1.0000
   6.250   0.8339   0.02561   0.01635  -0.0272   0.3739   1.0000
   6.500   0.8508   0.02680   0.01725  -0.0246   0.3206   1.0000
   6.750   0.8668   0.02823   0.01858  -0.0222   0.2708   1.0000
   7.000   0.8849   0.03005   0.02017  -0.0201   0.2281   1.0000
   7.250   0.9024   0.03217   0.02228  -0.0182   0.1921   1.0000
   7.500   0.9200   0.03431   0.02432  -0.0164   0.1616   1.0000
   7.750   0.9380   0.03710   0.02729  -0.0147   0.1402   1.0000
   8.000   0.9551   0.03994   0.03031  -0.0130   0.1232   1.0000
   8.250   0.9702   0.04385   0.03465  -0.0111   0.1147   1.0000
   8.500   0.9835   0.04701   0.03797  -0.0095   0.1039   1.0000
   8.750   0.9879   0.05060   0.04216  -0.0072   0.0978   1.0000
   9.000   0.9976   0.05470   0.04652  -0.0056   0.0945   1.0000
   9.250   1.0056   0.05985   0.05185  -0.0044   0.0928   1.0000
   9.500   0.9838   0.06433   0.05714  -0.0016   0.0953   1.0000
   9.750   0.9603   0.06967   0.06289  -0.0001   0.0975   1.0000
  10.000   0.9346   0.07462   0.06806   0.0008   0.0998   1.0000
  10.250   0.9104   0.07968   0.07323   0.0006   0.1016   1.0000
  10.500   0.8914   0.08535   0.07894  -0.0012   0.1034   1.0000
  10.750   0.8794   0.09146   0.08506  -0.0035   0.1048   1.0000
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