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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 200,000
Max Cl/Cd: 62.85 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg14a147-il-200000.txt
Download as CSV file: xf-rg14a147-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14A-1.4/7.0 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5161   0.08689   0.08342  -0.0147   1.0000   0.0357
  -8.000  -0.5176   0.08319   0.07977  -0.0166   1.0000   0.0366
  -7.750  -0.5221   0.07944   0.07608  -0.0188   1.0000   0.0373
  -7.500  -0.5246   0.07509   0.07176  -0.0225   1.0000   0.0381
  -7.250  -0.5233   0.07049   0.06713  -0.0262   1.0000   0.0393
  -7.000  -0.5189   0.06535   0.06186  -0.0310   1.0000   0.0414
  -6.750  -0.5121   0.06195   0.05811  -0.0335   1.0000   0.0426
  -6.500  -0.5094   0.05703   0.05296  -0.0339   1.0000   0.0431
  -6.250  -0.5041   0.05137   0.04744  -0.0335   1.0000   0.0447
  -6.000  -0.4930   0.04851   0.04458  -0.0327   1.0000   0.0463
  -5.750  -0.4806   0.04550   0.04145  -0.0321   1.0000   0.0489
  -5.250  -0.4536   0.03816   0.03346  -0.0309   1.0000   0.0582
  -5.000  -0.4375   0.03564   0.03088  -0.0298   1.0000   0.0614
  -4.750  -0.4208   0.03290   0.02762  -0.0287   1.0000   0.0708
  -4.500  -0.3922   0.02566   0.01945  -0.0251   1.0000   0.0294
  -4.250  -0.3720   0.02208   0.01542  -0.0237   1.0000   0.0271
  -4.000  -0.3489   0.02075   0.01372  -0.0223   1.0000   0.0296
  -3.750  -0.3256   0.01929   0.01193  -0.0209   1.0000   0.0303
  -3.500  -0.3020   0.01710   0.00949  -0.0197   1.0000   0.0301
  -3.000  -0.2560   0.01372   0.00595  -0.0172   1.0000   0.0336
  -2.750  -0.2334   0.01305   0.00526  -0.0162   1.0000   0.0407
  -2.500  -0.2103   0.01216   0.00435  -0.0152   1.0000   0.0550
  -2.250  -0.1891   0.01004   0.00358  -0.0149   1.0000   0.3378
  -2.000  -0.1763   0.00860   0.00363  -0.0120   1.0000   0.6877
  -1.750  -0.1681   0.00835   0.00395  -0.0064   1.0000   0.9006
  -1.500  -0.0881   0.00837   0.00377  -0.0162   1.0000   1.0000
  -1.250  -0.0765   0.00840   0.00365  -0.0137   1.0000   1.0000
  -1.000  -0.0611   0.00849   0.00363  -0.0119   1.0000   1.0000
  -0.750  -0.0241   0.00865   0.00366  -0.0144   0.9956   1.0000
  -0.500   0.0225   0.00878   0.00367  -0.0186   0.9880   1.0000
  -0.250   0.0703   0.00889   0.00368  -0.0230   0.9810   1.0000
   0.000   0.1155   0.00890   0.00363  -0.0267   0.9719   1.0000
   0.250   0.1605   0.00886   0.00357  -0.0303   0.9624   1.0000
   0.500   0.2113   0.00878   0.00348  -0.0350   0.9557   1.0000
   0.750   0.2554   0.00863   0.00334  -0.0382   0.9445   1.0000
   1.000   0.2978   0.00846   0.00318  -0.0410   0.9317   1.0000
   1.250   0.3388   0.00828   0.00303  -0.0434   0.9163   1.0000
   1.500   0.3731   0.00815   0.00293  -0.0443   0.8947   1.0000
   1.750   0.4044   0.00806   0.00284  -0.0445   0.8702   1.0000
   2.000   0.4312   0.00805   0.00279  -0.0437   0.8419   1.0000
   2.250   0.4556   0.00811   0.00278  -0.0425   0.8106   1.0000
   2.500   0.4790   0.00821   0.00280  -0.0411   0.7772   1.0000
   2.750   0.5019   0.00839   0.00291  -0.0397   0.7424   1.0000
   3.000   0.5242   0.00858   0.00303  -0.0382   0.7047   1.0000
   3.250   0.5464   0.00879   0.00314  -0.0368   0.6626   1.0000
   3.500   0.5683   0.00907   0.00327  -0.0353   0.6181   1.0000
   3.750   0.5902   0.00939   0.00345  -0.0339   0.5689   1.0000
   4.000   0.6119   0.00977   0.00371  -0.0325   0.5163   1.0000
   4.250   0.6331   0.01022   0.00396  -0.0312   0.4563   1.0000
   4.500   0.6527   0.01085   0.00423  -0.0297   0.3726   1.0000
   4.750   0.6725   0.01160   0.00460  -0.0284   0.2844   1.0000
   5.000   0.6932   0.01239   0.00508  -0.0274   0.2090   1.0000
   5.250   0.7116   0.01365   0.00582  -0.0262   0.1082   1.0000
   5.500   0.7289   0.01534   0.00718  -0.0244   0.0535   1.0000
   5.750   0.7496   0.01648   0.00838  -0.0231   0.0438   1.0000
   6.000   0.7675   0.01834   0.01023  -0.0214   0.0385   1.0000
   6.250   0.7909   0.01929   0.01134  -0.0204   0.0342   1.0000
   6.500   0.8130   0.02064   0.01276  -0.0193   0.0303   1.0000
   6.750   0.8341   0.02372   0.01597  -0.0181   0.0279   1.0000
   7.000   0.8566   0.02567   0.01827  -0.0169   0.0257   1.0000
   7.250   0.8782   0.02763   0.02058  -0.0156   0.0233   1.0000
   7.500   0.8966   0.03088   0.02429  -0.0139   0.0229   1.0000
   7.750   0.9105   0.03497   0.02899  -0.0118   0.0235   1.0000
   8.000   0.9191   0.03975   0.03430  -0.0095   0.0248   1.0000
   8.250   0.9202   0.04577   0.04073  -0.0076   0.0266   1.0000
  11.500   0.6900   0.12285   0.11981  -0.0253   0.0506   1.0000
  11.750   0.6834   0.12861   0.12555  -0.0288   0.0505   1.0000
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