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RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: RG 14 AIRFOIL (rg14-il)
Reynolds number: 200,000
Max Cl/Cd: 64.54 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg14-il-200000.txt
Download as CSV file: xf-rg14-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4036   0.10859   0.10513  -0.0187   1.0000   0.0440
 -10.250  -0.4107   0.10465   0.10122  -0.0220   1.0000   0.0449
 -10.000  -0.4167   0.10051   0.09714  -0.0249   1.0000   0.0452
  -9.750  -0.4189   0.09625   0.09291  -0.0269   1.0000   0.0453
  -9.500  -0.4232   0.09176   0.08845  -0.0293   1.0000   0.0454
  -9.250  -0.4154   0.08606   0.08274  -0.0261   1.0000   0.0471
  -9.000  -0.4100   0.08272   0.07941  -0.0255   1.0000   0.0483
  -8.750  -0.4092   0.07897   0.07569  -0.0259   1.0000   0.0495
  -8.500  -0.4114   0.07496   0.07171  -0.0269   1.0000   0.0507
  -8.250  -0.4163   0.07068   0.06747  -0.0282   1.0000   0.0518
  -8.000  -0.4244   0.06625   0.06308  -0.0300   1.0000   0.0528
  -7.750  -0.4378   0.06166   0.05855  -0.0323   1.0000   0.0534
  -7.500  -0.4567   0.05727   0.05419  -0.0341   1.0000   0.0535
  -7.250  -0.4697   0.05239   0.04927  -0.0358   1.0000   0.0545
  -7.000  -0.4916   0.04758   0.04408  -0.0378   1.0000   0.0575
  -6.750  -0.4960   0.04466   0.04084  -0.0363   1.0000   0.0580
  -6.500  -0.4958   0.03746   0.03381  -0.0357   1.0000   0.0597
  -6.250  -0.5208   0.04679   0.04269  -0.0345   1.0000   0.0603
  -6.000  -0.5101   0.04426   0.04014  -0.0331   1.0000   0.0621
  -5.750  -0.4996   0.04150   0.03722  -0.0316   1.0000   0.0649
  -5.500  -0.4878   0.03178   0.02605  -0.0275   1.0000   0.0336
  -5.250  -0.4747   0.02696   0.02098  -0.0260   1.0000   0.0300
  -5.000  -0.4570   0.02365   0.01717  -0.0241   1.0000   0.0281
  -4.750  -0.4366   0.02112   0.01420  -0.0224   1.0000   0.0277
  -4.500  -0.4149   0.01926   0.01203  -0.0209   1.0000   0.0277
  -4.250  -0.3930   0.01786   0.01043  -0.0196   1.0000   0.0289
  -4.000  -0.3711   0.01714   0.00955  -0.0183   1.0000   0.0322
  -3.750  -0.3494   0.01561   0.00794  -0.0172   1.0000   0.0359
  -3.500  -0.3277   0.01470   0.00699  -0.0160   1.0000   0.0407
  -3.250  -0.3062   0.01371   0.00599  -0.0148   1.0000   0.0532
  -3.000  -0.2848   0.01289   0.00534  -0.0139   1.0000   0.0932
  -2.750  -0.2640   0.01224   0.00504  -0.0131   1.0000   0.1576
  -2.500  -0.2325   0.01129   0.00485  -0.0149   0.9967   0.3232
  -2.250  -0.1996   0.01016   0.00486  -0.0165   0.9909   0.5885
  -2.000  -0.1705   0.00978   0.00526  -0.0156   0.9839   0.8163
  -1.750  -0.1389   0.00983   0.00536  -0.0152   0.9760   0.8997
  -1.500  -0.0877   0.00999   0.00544  -0.0190   0.9731   0.9549
  -1.250  -0.0204   0.01012   0.00540  -0.0266   0.9739   0.9830
  -1.000   0.0489   0.01015   0.00526  -0.0350   0.9756   1.0000
  -0.750   0.0983   0.01009   0.00510  -0.0396   0.9697   1.0000
  -0.500   0.1408   0.00994   0.00487  -0.0428   0.9598   1.0000
  -0.250   0.1869   0.00978   0.00465  -0.0466   0.9518   1.0000
   0.000   0.2349   0.00957   0.00440  -0.0507   0.9443   1.0000
   0.250   0.2764   0.00934   0.00415  -0.0534   0.9327   1.0000
   0.500   0.3166   0.00911   0.00389  -0.0557   0.9194   1.0000
   0.750   0.3542   0.00889   0.00365  -0.0575   0.9034   1.0000
   1.000   0.3854   0.00873   0.00347  -0.0578   0.8830   1.0000
   1.250   0.4136   0.00862   0.00330  -0.0576   0.8612   1.0000
   1.500   0.4373   0.00858   0.00321  -0.0564   0.8365   1.0000
   1.750   0.4598   0.00859   0.00315  -0.0550   0.8110   1.0000
   2.000   0.4815   0.00864   0.00312  -0.0535   0.7849   1.0000
   2.250   0.5026   0.00872   0.00314  -0.0519   0.7581   1.0000
   2.500   0.5233   0.00883   0.00316  -0.0502   0.7307   1.0000
   2.750   0.5439   0.00898   0.00321  -0.0485   0.7023   1.0000
   3.000   0.5645   0.00914   0.00329  -0.0469   0.6731   1.0000
   3.250   0.5852   0.00934   0.00338  -0.0453   0.6431   1.0000
   3.500   0.6058   0.00956   0.00353  -0.0437   0.6125   1.0000
   3.750   0.6266   0.00980   0.00368  -0.0421   0.5801   1.0000
   4.000   0.6476   0.01007   0.00385  -0.0406   0.5469   1.0000
   4.250   0.6687   0.01037   0.00404  -0.0392   0.5122   1.0000
   4.500   0.6899   0.01069   0.00426  -0.0379   0.4761   1.0000
   4.750   0.7113   0.01104   0.00455  -0.0366   0.4385   1.0000
   5.000   0.7326   0.01144   0.00484  -0.0354   0.3992   1.0000
   5.250   0.7538   0.01188   0.00516  -0.0342   0.3580   1.0000
   5.500   0.7748   0.01238   0.00552  -0.0330   0.3156   1.0000
   5.750   0.7956   0.01294   0.00594  -0.0319   0.2716   1.0000
   6.000   0.8158   0.01361   0.00642  -0.0307   0.2262   1.0000
   6.250   0.8361   0.01433   0.00697  -0.0296   0.1819   1.0000
   6.500   0.8559   0.01515   0.00765  -0.0285   0.1415   1.0000
   6.750   0.8754   0.01606   0.00841  -0.0273   0.1084   1.0000
   7.000   0.8937   0.01715   0.00937  -0.0259   0.0817   1.0000
   7.250   0.9123   0.01823   0.01041  -0.0245   0.0590   1.0000
   7.500   0.9272   0.01977   0.01186  -0.0226   0.0434   1.0000
   7.750   0.9448   0.02105   0.01320  -0.0210   0.0337   1.0000
   8.000   0.9620   0.02265   0.01495  -0.0192   0.0283   1.0000
   8.250   0.9785   0.02413   0.01645  -0.0178   0.0233   1.0000
   8.500   0.9944   0.02691   0.01947  -0.0160   0.0214   1.0000
   8.750   1.0133   0.02888   0.02170  -0.0146   0.0203   1.0000
   9.000   1.0304   0.03129   0.02442  -0.0131   0.0195   1.0000
   9.250   1.0444   0.03413   0.02761  -0.0113   0.0191   1.0000
   9.500   1.0543   0.03737   0.03125  -0.0092   0.0191   1.0000
   9.750   1.0583   0.04096   0.03527  -0.0066   0.0192   1.0000
  10.000   1.0563   0.04478   0.03950  -0.0039   0.0195   1.0000
  10.250   1.0484   0.04864   0.04372  -0.0010   0.0199   1.0000
  10.500   1.0341   0.05212   0.04747   0.0024   0.0202   1.0000
  10.750   1.0168   0.05569   0.05128   0.0050   0.0205   1.0000
  11.000   0.9968   0.05972   0.05552   0.0063   0.0206   1.0000
  11.250   0.9769   0.06422   0.06021   0.0059   0.0209   1.0000
  11.500   0.9562   0.06943   0.06559   0.0039   0.0210   1.0000
  11.750   0.9353   0.07561   0.07193   0.0003   0.0212   1.0000
  12.000   0.9142   0.08286   0.07931  -0.0047   0.0213   1.0000
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