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RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG 14 AIRFOIL (rg14-il)
Reynolds number: 100,000
Max Cl/Cd: 47.58 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg14-il-100000-n5.txt
Download as CSV file: xf-rg14-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5006   0.11540   0.11014  -0.0125   1.0000   0.0299
 -10.250  -0.4986   0.11122   0.10599  -0.0137   1.0000   0.0279
 -10.000  -0.4999   0.10630   0.10112  -0.0159   1.0000   0.0259
  -9.500  -0.5048   0.09532   0.09024  -0.0220   1.0000   0.0223
  -9.250  -0.5055   0.09120   0.08616  -0.0235   1.0000   0.0219
  -9.000  -0.5074   0.08688   0.08191  -0.0253   1.0000   0.0216
  -8.750  -0.5111   0.08232   0.07740  -0.0275   1.0000   0.0213
  -8.500  -0.5164   0.07764   0.07280  -0.0301   1.0000   0.0211
  -8.250  -0.5255   0.07281   0.06803  -0.0334   1.0000   0.0208
  -8.000  -0.5342   0.06777   0.06299  -0.0358   1.0000   0.0205
  -7.750  -0.5407   0.06274   0.05791  -0.0373   1.0000   0.0202
  -7.500  -0.5453   0.05791   0.05296  -0.0379   1.0000   0.0199
  -7.250  -0.5481   0.05309   0.04796  -0.0379   1.0000   0.0197
  -7.000  -0.5479   0.04845   0.04307  -0.0372   1.0000   0.0194
  -6.750  -0.5447   0.04400   0.03828  -0.0362   1.0000   0.0193
  -6.500  -0.5383   0.03983   0.03371  -0.0348   1.0000   0.0192
  -6.250  -0.5287   0.03599   0.02940  -0.0331   1.0000   0.0192
  -6.000  -0.5158   0.03265   0.02558  -0.0315   1.0000   0.0194
  -5.750  -0.5001   0.02970   0.02213  -0.0298   1.0000   0.0199
  -5.500  -0.4816   0.02756   0.01948  -0.0283   1.0000   0.0215
  -5.250  -0.4621   0.02565   0.01715  -0.0268   1.0000   0.0232
  -5.000  -0.4429   0.02375   0.01508  -0.0256   1.0000   0.0249
  -4.750  -0.4222   0.02220   0.01334  -0.0243   1.0000   0.0263
  -4.500  -0.4012   0.02085   0.01183  -0.0230   1.0000   0.0280
  -4.250  -0.3802   0.01965   0.01048  -0.0216   1.0000   0.0303
  -4.000  -0.3595   0.01855   0.00922  -0.0202   1.0000   0.0338
  -3.750  -0.3387   0.01774   0.00838  -0.0191   1.0000   0.0439
  -3.500  -0.3179   0.01690   0.00753  -0.0180   1.0000   0.0605
  -3.250  -0.2968   0.01619   0.00693  -0.0170   1.0000   0.0874
  -3.000  -0.2755   0.01555   0.00644  -0.0161   1.0000   0.1264
  -2.750  -0.2470   0.01484   0.00607  -0.0169   0.9968   0.2001
  -2.500  -0.2129   0.01407   0.00581  -0.0188   0.9903   0.3261
  -2.250  -0.1810   0.01313   0.00569  -0.0200   0.9837   0.5222
  -2.000  -0.1564   0.01254   0.00590  -0.0181   0.9760   0.7468
  -1.750  -0.1224   0.01257   0.00599  -0.0182   0.9692   0.8590
  -1.500  -0.0810   0.01260   0.00595  -0.0201   0.9626   0.9205
  -1.250  -0.0233   0.01265   0.00583  -0.0257   0.9598   0.9618
  -1.000   0.0396   0.01263   0.00560  -0.0328   0.9577   0.9885
  -0.750   0.0876   0.01257   0.00539  -0.0371   0.9501   1.0000
  -0.500   0.1271   0.01249   0.00519  -0.0397   0.9397   1.0000
  -0.250   0.1668   0.01239   0.00500  -0.0422   0.9289   1.0000
   0.000   0.2027   0.01228   0.00483  -0.0439   0.9154   1.0000
   0.250   0.2371   0.01217   0.00467  -0.0452   0.9002   1.0000
   0.500   0.2699   0.01208   0.00453  -0.0461   0.8831   1.0000
   0.750   0.3027   0.01200   0.00440  -0.0470   0.8653   1.0000
   1.000   0.3353   0.01192   0.00428  -0.0477   0.8470   1.0000
   1.250   0.3635   0.01190   0.00424  -0.0476   0.8256   1.0000
   1.500   0.3923   0.01188   0.00417  -0.0475   0.8042   1.0000
   1.750   0.4182   0.01191   0.00415  -0.0468   0.7806   1.0000
   2.000   0.4435   0.01197   0.00416  -0.0460   0.7561   1.0000
   2.250   0.4683   0.01206   0.00423  -0.0451   0.7308   1.0000
   2.500   0.4923   0.01218   0.00428  -0.0441   0.7046   1.0000
   2.750   0.5158   0.01233   0.00437  -0.0430   0.6772   1.0000
   3.000   0.5390   0.01251   0.00448  -0.0418   0.6489   1.0000
   3.250   0.5618   0.01271   0.00462  -0.0406   0.6195   1.0000
   3.500   0.5845   0.01295   0.00484  -0.0393   0.5890   1.0000
   3.750   0.6070   0.01322   0.00503  -0.0381   0.5575   1.0000
   4.000   0.6293   0.01351   0.00526  -0.0369   0.5248   1.0000
   4.250   0.6514   0.01384   0.00552  -0.0357   0.4909   1.0000
   4.500   0.6733   0.01421   0.00581  -0.0345   0.4559   1.0000
   4.750   0.6950   0.01462   0.00613  -0.0332   0.4199   1.0000
   5.000   0.7165   0.01506   0.00655  -0.0321   0.3824   1.0000
   5.250   0.7378   0.01555   0.00696  -0.0309   0.3442   1.0000
   5.500   0.7588   0.01610   0.00742  -0.0298   0.3056   1.0000
   5.750   0.7795   0.01671   0.00793  -0.0286   0.2670   1.0000
   6.000   0.8000   0.01738   0.00851  -0.0275   0.2279   1.0000
   6.250   0.8203   0.01811   0.00915  -0.0265   0.1909   1.0000
   6.500   0.8401   0.01894   0.00994  -0.0253   0.1575   1.0000
   6.750   0.8598   0.01982   0.01075  -0.0242   0.1263   1.0000
   7.000   0.8789   0.02080   0.01166  -0.0231   0.1001   1.0000
   7.250   0.8971   0.02188   0.01267  -0.0219   0.0779   1.0000
   7.500   0.9152   0.02302   0.01384  -0.0205   0.0605   1.0000
   7.750   0.9316   0.02435   0.01523  -0.0189   0.0488   1.0000
   8.000   0.9480   0.02568   0.01660  -0.0175   0.0385   1.0000
   8.250   0.9609   0.02739   0.01836  -0.0156   0.0327   1.0000
   8.500   0.9777   0.02877   0.01997  -0.0141   0.0274   1.0000
   8.750   0.9917   0.03028   0.02164  -0.0126   0.0232   1.0000
   9.000   1.0031   0.03259   0.02411  -0.0106   0.0213   1.0000
   9.250   1.0173   0.03480   0.02662  -0.0089   0.0198   1.0000
   9.500   1.0302   0.03720   0.02931  -0.0073   0.0188   1.0000
   9.750   1.0403   0.03942   0.03181  -0.0055   0.0173   1.0000
  10.000   1.0479   0.04147   0.03407  -0.0038   0.0162   1.0000
  10.250   1.0511   0.04356   0.03631  -0.0018   0.0152   1.0000
  10.750   1.0420   0.04943   0.04268   0.0030   0.0142   1.0000
  11.000   1.0335   0.05255   0.04614   0.0048   0.0138   1.0000
  11.250   1.0223   0.05614   0.05001   0.0057   0.0138   1.0000
  11.500   1.0082   0.06029   0.05443   0.0056   0.0137   1.0000
  11.750   0.9931   0.06497   0.05934   0.0043   0.0137   1.0000
  12.000   0.9769   0.07037   0.06495   0.0018   0.0138   1.0000
  12.250   0.9595   0.07664   0.07141  -0.0019   0.0139   1.0000
  12.500   0.9406   0.08402   0.07896  -0.0069   0.0139   1.0000
  12.750   0.9215   0.09232   0.08739  -0.0126   0.0141   1.0000
  13.000   0.9032   0.10113   0.09628  -0.0184   0.0143   1.0000
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