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RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAE 5214 AIRFOIL (rae5214-il)
Reynolds number: 200,000
Max Cl/Cd: 49.13 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5214-il-200000-n5.txt
Download as CSV file: xf-rae5214-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 5214 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5702   0.08385   0.07983  -0.0288   1.0000   0.0167
 -10.000  -0.5852   0.07485   0.07088  -0.0348   1.0000   0.0165
  -9.750  -0.6147   0.06338   0.05932  -0.0440   1.0000   0.0163
  -9.500  -0.6415   0.05689   0.05271  -0.0482   1.0000   0.0161
  -9.250  -0.6683   0.05161   0.04725  -0.0494   1.0000   0.0160
  -9.000  -0.6859   0.04602   0.04133  -0.0495   1.0000   0.0161
  -8.750  -0.6970   0.04048   0.03535  -0.0487   1.0000   0.0162
  -8.500  -0.7016   0.03509   0.02932  -0.0473   1.0000   0.0166
  -8.250  -0.6934   0.03202   0.02583  -0.0460   1.0000   0.0172
  -8.000  -0.6765   0.03116   0.02495  -0.0450   1.0000   0.0177
  -7.750  -0.6608   0.02977   0.02340  -0.0439   1.0000   0.0183
  -7.500  -0.6461   0.02763   0.02090  -0.0425   1.0000   0.0191
  -7.250  -0.6306   0.02516   0.01788  -0.0410   1.0000   0.0200
  -7.000  -0.6126   0.02388   0.01651  -0.0397   1.0000   0.0204
  -6.750  -0.5939   0.02287   0.01543  -0.0385   1.0000   0.0210
  -6.500  -0.5748   0.02190   0.01435  -0.0372   1.0000   0.0218
  -6.250  -0.5528   0.02085   0.01303  -0.0364   0.9994   0.0232
  -6.000  -0.5208   0.01987   0.01203  -0.0377   0.9962   0.0244
  -5.750  -0.4887   0.01892   0.01101  -0.0389   0.9930   0.0255
  -5.500  -0.4572   0.01797   0.00993  -0.0398   0.9894   0.0268
  -5.250  -0.4246   0.01721   0.00920  -0.0412   0.9862   0.0284
  -5.000  -0.3925   0.01659   0.00854  -0.0423   0.9825   0.0304
  -4.750  -0.3608   0.01587   0.00781  -0.0433   0.9782   0.0319
  -4.500  -0.3272   0.01530   0.00726  -0.0448   0.9751   0.0338
  -4.250  -0.2962   0.01478   0.00671  -0.0456   0.9703   0.0363
  -4.000  -0.2638   0.01427   0.00622  -0.0468   0.9658   0.0387
  -3.750  -0.2290   0.01381   0.00575  -0.0483   0.9628   0.0421
  -3.500  -0.1984   0.01341   0.00535  -0.0490   0.9573   0.0462
  -3.250  -0.1653   0.01299   0.00494  -0.0502   0.9529   0.0522
  -3.000  -0.1307   0.01253   0.00455  -0.0516   0.9495   0.0662
  -2.750  -0.1015   0.01199   0.00423  -0.0522   0.9432   0.1106
  -2.500  -0.0711   0.01097   0.00385  -0.0535   0.9380   0.2636
  -2.250  -0.0406   0.00999   0.00379  -0.0545   0.9340   0.4874
  -2.000  -0.0139   0.00992   0.00394  -0.0540   0.9262   0.5670
  -1.750   0.0170   0.01001   0.00414  -0.0541   0.9208   0.6213
  -1.500   0.0463   0.01014   0.00434  -0.0538   0.9148   0.6541
  -1.250   0.0753   0.01016   0.00438  -0.0536   0.9073   0.6682
  -1.000   0.1074   0.01009   0.00423  -0.0540   0.8979   0.6753
  -0.750   0.1382   0.00997   0.00408  -0.0540   0.8846   0.6798
  -0.500   0.1666   0.00988   0.00395  -0.0535   0.8677   0.6851
  -0.250   0.1950   0.00982   0.00380  -0.0531   0.8487   0.6907
   0.000   0.2218   0.00975   0.00367  -0.0523   0.8250   0.6952
   0.250   0.2486   0.00971   0.00357  -0.0515   0.7995   0.6999
   0.500   0.2755   0.00972   0.00347  -0.0507   0.7715   0.7051
   0.750   0.3024   0.00975   0.00340  -0.0501   0.7412   0.7104
   1.000   0.3285   0.00980   0.00336  -0.0493   0.7074   0.7145
   1.250   0.3541   0.00991   0.00332  -0.0484   0.6620   0.7194
   1.500   0.3781   0.01018   0.00328  -0.0472   0.5879   0.7247
   1.750   0.3985   0.01077   0.00333  -0.0456   0.4720   0.7293
   2.000   0.4184   0.01153   0.00355  -0.0442   0.3497   0.7339
   2.250   0.4402   0.01225   0.00381  -0.0433   0.2497   0.7394
   2.750   0.4894   0.01309   0.00427  -0.0422   0.1759   0.7496
   3.000   0.5148   0.01340   0.00451  -0.0417   0.1579   0.7555
   3.250   0.5407   0.01369   0.00475  -0.0413   0.1439   0.7620
   3.500   0.5662   0.01394   0.00501  -0.0408   0.1331   0.7676
   3.750   0.5916   0.01423   0.00527  -0.0403   0.1244   0.7742
   4.000   0.6171   0.01451   0.00556  -0.0398   0.1168   0.7814
   4.250   0.6420   0.01480   0.00587  -0.0392   0.1108   0.7895
   4.500   0.6671   0.01509   0.00619  -0.0387   0.1049   0.7983
   4.750   0.6913   0.01545   0.00653  -0.0380   0.0996   0.8082
   5.000   0.7164   0.01572   0.00689  -0.0374   0.0942   0.8194
   5.250   0.7402   0.01609   0.00726  -0.0366   0.0889   0.8345
   5.500   0.7645   0.01630   0.00760  -0.0358   0.0838   0.8560
   5.750   0.7884   0.01655   0.00794  -0.0350   0.0792   0.8979
   6.000   0.8185   0.01689   0.00836  -0.0356   0.0744   1.0000
   6.250   0.8442   0.01731   0.00875  -0.0353   0.0701   1.0000
   6.500   0.8695   0.01777   0.00925  -0.0350   0.0661   1.0000
   6.750   0.8946   0.01821   0.00968  -0.0347   0.0622   1.0000
   7.000   0.9193   0.01873   0.01022  -0.0342   0.0587   1.0000
   7.250   0.9437   0.01923   0.01074  -0.0338   0.0555   1.0000
   7.500   0.9675   0.01984   0.01136  -0.0333   0.0527   1.0000
   7.750   0.9913   0.02042   0.01199  -0.0327   0.0498   1.0000
   8.000   1.0143   0.02107   0.01263  -0.0321   0.0475   1.0000
   8.250   1.0374   0.02177   0.01342  -0.0315   0.0451   1.0000
   8.500   1.0599   0.02245   0.01414  -0.0308   0.0432   1.0000
   8.750   1.0814   0.02327   0.01498  -0.0301   0.0418   1.0000
   9.000   1.1030   0.02415   0.01599  -0.0292   0.0403   1.0000
   9.250   1.1240   0.02503   0.01696  -0.0284   0.0390   1.0000
   9.500   1.1444   0.02590   0.01787  -0.0275   0.0380   1.0000
   9.750   1.1637   0.02686   0.01884  -0.0266   0.0371   1.0000
  10.000   1.1831   0.02795   0.02013  -0.0256   0.0361   1.0000
  10.250   1.2016   0.02906   0.02139  -0.0246   0.0351   1.0000
  10.500   1.2192   0.03014   0.02259  -0.0235   0.0343   1.0000
  10.750   1.2358   0.03124   0.02378  -0.0223   0.0336   1.0000
  11.000   1.2513   0.03239   0.02501  -0.0210   0.0331   1.0000
  11.250   1.2654   0.03365   0.02632  -0.0197   0.0326   1.0000
  11.500   1.2769   0.03527   0.02817  -0.0181   0.0322   1.0000
  11.750   1.2850   0.03698   0.03012  -0.0161   0.0317   1.0000
  12.000   1.2896   0.03878   0.03215  -0.0138   0.0314   1.0000
  12.250   1.2915   0.04073   0.03430  -0.0115   0.0310   1.0000
  12.500   1.2912   0.04278   0.03657  -0.0094   0.0307   1.0000
  12.750   1.2888   0.04506   0.03905  -0.0075   0.0304   1.0000
  13.000   1.2846   0.04757   0.04175  -0.0061   0.0301   1.0000
  13.250   1.2783   0.05043   0.04480  -0.0052   0.0299   1.0000
  13.500   1.2700   0.05369   0.04825  -0.0048   0.0296   1.0000
  13.750   1.2591   0.05754   0.05228  -0.0053   0.0295   1.0000
  14.000   1.2450   0.06219   0.05712  -0.0067   0.0293   1.0000
  14.250   1.2243   0.06836   0.06353  -0.0097   0.0293   1.0000
  14.500   1.1787   0.08024   0.07578  -0.0177   0.0294   1.0000
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