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RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG 14 9% AIRFOIL (rg149-il)
Reynolds number: 50,000
Max Cl/Cd: 34.12 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg149-il-50000-n5.txt
Download as CSV file: xf-rg149-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9% 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5414   0.08639   0.07931  -0.0346   1.0000   0.0508
  -9.000  -0.5475   0.08166   0.07463  -0.0368   1.0000   0.0506
  -8.750  -0.5551   0.07754   0.07055  -0.0377   1.0000   0.0503
  -8.500  -0.5632   0.07312   0.06611  -0.0387   1.0000   0.0501
  -8.250  -0.5696   0.06884   0.06178  -0.0393   1.0000   0.0498
  -8.000  -0.5758   0.06445   0.05727  -0.0395   1.0000   0.0496
  -7.750  -0.5793   0.06019   0.05284  -0.0393   1.0000   0.0495
  -7.500  -0.5806   0.05594   0.04833  -0.0386   1.0000   0.0495
  -7.250  -0.5789   0.05181   0.04383  -0.0377   1.0000   0.0496
  -7.000  -0.5743   0.04783   0.03940  -0.0365   1.0000   0.0501
  -6.750  -0.5662   0.04438   0.03560  -0.0352   1.0000   0.0518
  -6.500  -0.5524   0.04234   0.03351  -0.0340   1.0000   0.0547
  -6.250  -0.5387   0.03959   0.03040  -0.0327   1.0000   0.0569
  -6.000  -0.5232   0.03665   0.02699  -0.0313   1.0000   0.0582
  -5.750  -0.5052   0.03398   0.02384  -0.0298   1.0000   0.0599
  -5.500  -0.4852   0.03165   0.02101  -0.0284   1.0000   0.0621
  -5.250  -0.4655   0.02992   0.01914  -0.0273   1.0000   0.0665
  -5.000  -0.4448   0.02848   0.01751  -0.0261   1.0000   0.0719
  -4.750  -0.4221   0.02690   0.01554  -0.0247   1.0000   0.0762
  -4.500  -0.4010   0.02551   0.01418  -0.0234   1.0000   0.0814
  -4.250  -0.3791   0.02440   0.01288  -0.0220   1.0000   0.0904
  -4.000  -0.3582   0.02338   0.01187  -0.0208   1.0000   0.1051
  -3.750  -0.3371   0.02233   0.01089  -0.0197   1.0000   0.1252
  -3.500  -0.3162   0.02130   0.01000  -0.0188   1.0000   0.1634
  -3.250  -0.2972   0.02021   0.00930  -0.0177   1.0000   0.2283
  -3.000  -0.2797   0.01907   0.00875  -0.0163   1.0000   0.3343
  -2.750  -0.2654   0.01794   0.00846  -0.0138   1.0000   0.4931
  -2.500  -0.2538   0.01725   0.00875  -0.0087   1.0000   0.7023
  -2.250  -0.2279   0.01731   0.00889  -0.0062   1.0000   0.8690
  -2.000  -0.1328   0.01749   0.00857  -0.0177   1.0000   0.9801
  -1.750  -0.0965   0.01742   0.00820  -0.0202   1.0000   1.0000
  -1.500  -0.0904   0.01738   0.00799  -0.0172   1.0000   1.0000
  -1.250  -0.0828   0.01740   0.00785  -0.0144   1.0000   1.0000
  -1.000  -0.0731   0.01748   0.00776  -0.0121   1.0000   1.0000
  -0.750  -0.0570   0.01763   0.00775  -0.0109   0.9984   1.0000
  -0.500  -0.0128   0.01794   0.00786  -0.0150   0.9862   1.0000
  -0.250   0.0298   0.01821   0.00797  -0.0186   0.9734   1.0000
   0.000   0.0713   0.01843   0.00807  -0.0218   0.9601   1.0000
   0.250   0.1119   0.01862   0.00817  -0.0248   0.9464   1.0000
   0.500   0.1525   0.01878   0.00826  -0.0277   0.9322   1.0000
   0.750   0.1929   0.01890   0.00834  -0.0304   0.9179   1.0000
   1.000   0.2338   0.01897   0.00841  -0.0330   0.9034   1.0000
   1.250   0.2746   0.01901   0.00846  -0.0355   0.8886   1.0000
   1.500   0.3135   0.01901   0.00850  -0.0375   0.8730   1.0000
   1.750   0.3511   0.01900   0.00853  -0.0391   0.8569   1.0000
   2.000   0.3827   0.01903   0.00860  -0.0395   0.8379   1.0000
   2.250   0.4152   0.01904   0.00868  -0.0399   0.8188   1.0000
   2.500   0.4488   0.01901   0.00871  -0.0404   0.7999   1.0000
   2.750   0.4767   0.01907   0.00883  -0.0399   0.7779   1.0000
   3.000   0.5071   0.01907   0.00891  -0.0396   0.7565   1.0000
   3.250   0.5331   0.01915   0.00903  -0.0386   0.7312   1.0000
   3.500   0.5595   0.01917   0.00908  -0.0374   0.7022   1.0000
   3.750   0.5850   0.01921   0.00912  -0.0360   0.6700   1.0000
   4.000   0.6081   0.01935   0.00926  -0.0343   0.6362   1.0000
   4.250   0.6314   0.01957   0.00948  -0.0328   0.6041   1.0000
   4.500   0.6543   0.01984   0.00975  -0.0314   0.5718   1.0000
   4.750   0.6763   0.02017   0.01009  -0.0298   0.5367   1.0000
   5.000   0.6971   0.02055   0.01042  -0.0280   0.4978   1.0000
   5.250   0.7165   0.02100   0.01079  -0.0261   0.4545   1.0000
   5.500   0.7348   0.02156   0.01124  -0.0242   0.4079   1.0000
   5.750   0.7525   0.02224   0.01178  -0.0223   0.3596   1.0000
   6.000   0.7697   0.02307   0.01248  -0.0205   0.3124   1.0000
   6.250   0.7868   0.02403   0.01328  -0.0189   0.2697   1.0000
   6.500   0.8043   0.02510   0.01421  -0.0175   0.2336   1.0000
   6.750   0.8223   0.02626   0.01527  -0.0162   0.2044   1.0000
   7.000   0.8401   0.02748   0.01640  -0.0149   0.1801   1.0000
   7.250   0.8590   0.02878   0.01771  -0.0138   0.1605   1.0000
   7.500   0.8773   0.03015   0.01910  -0.0126   0.1433   1.0000
   7.750   0.8971   0.03161   0.02064  -0.0116   0.1293   1.0000
   8.000   0.9165   0.03308   0.02224  -0.0105   0.1166   1.0000
   8.250   0.9361   0.03465   0.02398  -0.0095   0.1058   1.0000
   8.500   0.9555   0.03637   0.02579  -0.0085   0.0973   1.0000
   8.750   0.9725   0.03795   0.02753  -0.0074   0.0887   1.0000
   9.000   0.9910   0.04025   0.03015  -0.0063   0.0821   1.0000
   9.250   1.0072   0.04234   0.03246  -0.0052   0.0763   1.0000
   9.500   1.0189   0.04477   0.03522  -0.0037   0.0704   1.0000
   9.750   1.0288   0.04736   0.03814  -0.0022   0.0656   1.0000
  10.000   1.0416   0.04976   0.04050  -0.0012   0.0617   1.0000
  10.250   1.0378   0.05325   0.04464   0.0012   0.0588   1.0000
  10.500   1.0330   0.05642   0.04819   0.0033   0.0556   1.0000
  10.750   1.0269   0.05935   0.05136   0.0053   0.0535   1.0000
  11.000   1.0194   0.06247   0.05467   0.0070   0.0522   1.0000
  11.250   1.0195   0.06523   0.05741   0.0080   0.0501   1.0000
  11.500   1.0004   0.06955   0.06197   0.0084   0.0498   1.0000
  11.750   0.9799   0.07449   0.06714   0.0075   0.0498   1.0000
  12.000   0.9581   0.08026   0.07309   0.0052   0.0499   1.0000
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