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RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RAE 5214 AIRFOIL (rae5214-il)
Reynolds number: 100,000
Max Cl/Cd: 35.69 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5214-il-100000-n5.txt
Download as CSV file: xf-rae5214-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5464   0.08519   0.07965  -0.0306   1.0000   0.0309
  -9.500  -0.5524   0.07899   0.07348  -0.0346   1.0000   0.0304
  -9.250  -0.5675   0.07173   0.06622  -0.0400   1.0000   0.0300
  -9.000  -0.5879   0.06586   0.06031  -0.0440   1.0000   0.0296
  -8.750  -0.6079   0.06105   0.05539  -0.0459   1.0000   0.0292
  -8.500  -0.6210   0.05626   0.05040  -0.0469   1.0000   0.0289
  -8.250  -0.6278   0.05181   0.04568  -0.0469   1.0000   0.0288
  -8.000  -0.6293   0.04769   0.04124  -0.0465   1.0000   0.0287
  -7.750  -0.6259   0.04394   0.03715  -0.0456   1.0000   0.0288
  -7.500  -0.6181   0.04069   0.03354  -0.0447   1.0000   0.0293
  -7.250  -0.6082   0.03749   0.02987  -0.0436   1.0000   0.0305
  -7.000  -0.5957   0.03442   0.02624  -0.0423   1.0000   0.0315
  -6.750  -0.5785   0.03289   0.02465  -0.0413   1.0000   0.0323
  -6.500  -0.5612   0.03092   0.02242  -0.0402   1.0000   0.0329
  -6.250  -0.5428   0.02901   0.02024  -0.0389   1.0000   0.0337
  -6.000  -0.5235   0.02723   0.01814  -0.0377   1.0000   0.0349
  -5.750  -0.5037   0.02583   0.01653  -0.0365   1.0000   0.0366
  -5.500  -0.4838   0.02482   0.01549  -0.0354   1.0000   0.0384
  -5.250  -0.4631   0.02360   0.01411  -0.0341   1.0000   0.0399
  -5.000  -0.4423   0.02248   0.01284  -0.0328   1.0000   0.0414
  -4.750  -0.4221   0.02168   0.01210  -0.0318   1.0000   0.0436
  -4.500  -0.4013   0.02089   0.01123  -0.0306   1.0000   0.0462
  -4.250  -0.3808   0.02005   0.01041  -0.0294   1.0000   0.0480
  -4.000  -0.3601   0.01940   0.00981  -0.0285   1.0000   0.0511
  -3.750  -0.3361   0.01877   0.00914  -0.0280   0.9990   0.0547
  -3.500  -0.3025   0.01811   0.00851  -0.0296   0.9946   0.0590
  -3.250  -0.2694   0.01750   0.00791  -0.0309   0.9897   0.0659
  -3.000  -0.2348   0.01694   0.00737  -0.0326   0.9854   0.0780
  -2.750  -0.2022   0.01624   0.00686  -0.0340   0.9801   0.1095
  -2.500  -0.1717   0.01443   0.00636  -0.0362   0.9760   0.3684
  -2.250  -0.1439   0.01417   0.00689  -0.0359   0.9700   0.5698
  -2.000  -0.1132   0.01453   0.00739  -0.0357   0.9639   0.6437
  -1.750  -0.0861   0.01490   0.00782  -0.0346   0.9570   0.6920
  -1.500  -0.0564   0.01508   0.00805  -0.0341   0.9512   0.7174
  -1.250  -0.0234   0.01507   0.00795  -0.0352   0.9452   0.7280
  -1.000   0.0089   0.01503   0.00787  -0.0359   0.9388   0.7343
  -0.750   0.0471   0.01500   0.00778  -0.0379   0.9344   0.7418
  -0.500   0.0769   0.01496   0.00771  -0.0383   0.9259   0.7482
  -0.250   0.1147   0.01489   0.00762  -0.0400   0.9199   0.7546
   0.000   0.1480   0.01481   0.00752  -0.0409   0.9099   0.7619
   0.250   0.1874   0.01458   0.00731  -0.0425   0.8991   0.7674
   0.500   0.2257   0.01429   0.00703  -0.0436   0.8841   0.7737
   0.750   0.2581   0.01402   0.00674  -0.0436   0.8627   0.7803
   1.000   0.2883   0.01371   0.00643  -0.0428   0.8351   0.7862
   1.250   0.3179   0.01347   0.00615  -0.0421   0.8039   0.7930
   1.500   0.3471   0.01332   0.00597  -0.0415   0.7759   0.7995
   1.750   0.3736   0.01323   0.00587  -0.0405   0.7437   0.8066
   2.000   0.4010   0.01318   0.00575  -0.0397   0.7016   0.8142
   2.250   0.4264   0.01320   0.00561  -0.0384   0.6352   0.8216
   2.750   0.4659   0.01448   0.00558  -0.0343   0.3611   0.8395
   3.000   0.4853   0.01536   0.00590  -0.0330   0.2583   0.8501
   3.250   0.5074   0.01594   0.00624  -0.0320   0.2143   0.8628
   3.500   0.5306   0.01640   0.00659  -0.0311   0.1901   0.8785
   3.750   0.5555   0.01682   0.00697  -0.0306   0.1726   0.8997
   4.250   0.6159   0.01777   0.00787  -0.0320   0.1465   1.0000
   4.500   0.6421   0.01837   0.00839  -0.0320   0.1374   1.0000
   4.750   0.6680   0.01896   0.00890  -0.0319   0.1293   1.0000
   5.000   0.6939   0.01958   0.00951  -0.0318   0.1220   1.0000
   5.250   0.7195   0.02021   0.01008  -0.0316   0.1154   1.0000
   5.500   0.7450   0.02091   0.01077  -0.0313   0.1092   1.0000
   5.750   0.7702   0.02158   0.01142  -0.0311   0.1031   1.0000
   6.000   0.7952   0.02234   0.01218  -0.0308   0.0974   1.0000
   6.250   0.8202   0.02303   0.01288  -0.0305   0.0916   1.0000
   6.500   0.8446   0.02385   0.01370  -0.0301   0.0865   1.0000
   6.750   0.8692   0.02462   0.01455  -0.0297   0.0813   1.0000
   7.000   0.8930   0.02549   0.01537  -0.0293   0.0773   1.0000
   7.250   0.9171   0.02640   0.01647  -0.0288   0.0727   1.0000
   7.500   0.9402   0.02722   0.01724  -0.0284   0.0695   1.0000
   7.750   0.9636   0.02843   0.01866  -0.0278   0.0657   1.0000
   8.000   0.9861   0.02936   0.01966  -0.0272   0.0627   1.0000
   8.250   1.0080   0.03046   0.02083  -0.0266   0.0602   1.0000
   8.500   1.0292   0.03198   0.02261  -0.0259   0.0575   1.0000
   8.750   1.0500   0.03327   0.02401  -0.0252   0.0557   1.0000
   9.000   1.0705   0.03437   0.02512  -0.0245   0.0542   1.0000
   9.250   1.0872   0.03655   0.02771  -0.0234   0.0522   1.0000
   9.500   1.1032   0.03843   0.02986  -0.0223   0.0504   1.0000
   9.750   1.1194   0.03990   0.03148  -0.0213   0.0491   1.0000
  10.000   1.1355   0.04138   0.03303  -0.0204   0.0482   1.0000
  10.250   1.1452   0.04393   0.03589  -0.0189   0.0474   1.0000
  10.500   1.1450   0.04758   0.04005  -0.0169   0.0466   1.0000
  10.750   1.1393   0.05137   0.04428  -0.0147   0.0459   1.0000
  11.000   1.1262   0.05521   0.04849  -0.0122   0.0455   1.0000
  11.250   1.1053   0.05923   0.05282  -0.0097   0.0452   1.0000
  11.500   1.0767   0.06430   0.05818  -0.0088   0.0451   1.0000
  11.750   1.0367   0.07166   0.06583  -0.0109   0.0453   1.0000
  12.000   0.9592   0.08891   0.08341  -0.0231   0.0462   1.0000
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