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RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RAE 5215 AIRFOIL (rae5215-il)
Reynolds number: 200,000
Max Cl/Cd: 49.81 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5215-il-200000-n5.txt
Download as CSV file: xf-rae5215-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE 5215 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6050   0.08988   0.08597  -0.0171   1.0000   0.0172
  -9.750  -0.6142   0.08229   0.07841  -0.0222   1.0000   0.0170
  -9.500  -0.6372   0.06946   0.06555  -0.0332   1.0000   0.0166
  -9.250  -0.6666   0.06017   0.05612  -0.0413   1.0000   0.0163
  -9.000  -0.6868   0.05268   0.04833  -0.0460   1.0000   0.0162
  -8.750  -0.6969   0.04581   0.04104  -0.0480   1.0000   0.0162
  -8.500  -0.6980   0.03975   0.03446  -0.0488   1.0000   0.0163
  -8.250  -0.6910   0.03476   0.02890  -0.0488   1.0000   0.0167
  -8.000  -0.6789   0.03034   0.02380  -0.0484   1.0000   0.0173
  -7.750  -0.6613   0.02768   0.02072  -0.0479   1.0000   0.0178
  -7.500  -0.6406   0.02670   0.01968  -0.0473   1.0000   0.0183
  -7.250  -0.6198   0.02563   0.01850  -0.0467   1.0000   0.0192
  -7.000  -0.5990   0.02399   0.01648  -0.0459   1.0000   0.0204
  -6.750  -0.5780   0.02277   0.01513  -0.0451   1.0000   0.0212
  -6.500  -0.5569   0.02187   0.01417  -0.0442   1.0000   0.0220
  -6.250  -0.5358   0.02093   0.01311  -0.0433   1.0000   0.0230
  -6.000  -0.5145   0.01996   0.01196  -0.0423   1.0000   0.0244
  -5.750  -0.4918   0.01923   0.01124  -0.0417   0.9996   0.0254
  -5.500  -0.4591   0.01828   0.01023  -0.0430   0.9967   0.0266
  -5.250  -0.4261   0.01739   0.00922  -0.0442   0.9941   0.0280
  -5.000  -0.3942   0.01664   0.00853  -0.0455   0.9906   0.0294
  -4.750  -0.3608   0.01606   0.00789  -0.0469   0.9874   0.0317
  -4.500  -0.3265   0.01543   0.00730  -0.0486   0.9848   0.0338
  -4.250  -0.2938   0.01493   0.00677  -0.0498   0.9808   0.0364
  -4.000  -0.2603   0.01438   0.00625  -0.0513   0.9773   0.0388
  -3.750  -0.2257   0.01392   0.00576  -0.0529   0.9746   0.0418
  -3.500  -0.1919   0.01349   0.00535  -0.0544   0.9713   0.0464
  -3.250  -0.1596   0.01309   0.00496  -0.0554   0.9666   0.0527
  -3.000  -0.1256   0.01265   0.00458  -0.0569   0.9630   0.0660
  -2.750  -0.0910   0.01205   0.00423  -0.0587   0.9602   0.1182
  -2.500  -0.0601   0.01092   0.00387  -0.0603   0.9554   0.2986
  -2.250  -0.0292   0.01014   0.00389  -0.0614   0.9508   0.4971
  -2.000   0.0029   0.01009   0.00407  -0.0620   0.9468   0.5777
  -1.750   0.0330   0.01021   0.00431  -0.0621   0.9416   0.6272
  -1.500   0.0629   0.01034   0.00446  -0.0620   0.9339   0.6576
  -1.250   0.0935   0.01031   0.00444  -0.0620   0.9247   0.6695
  -1.000   0.1239   0.01024   0.00430  -0.0621   0.9140   0.6759
  -0.750   0.1522   0.01018   0.00423  -0.0617   0.9028   0.6805
  -0.500   0.1806   0.01011   0.00412  -0.0613   0.8898   0.6858
  -0.250   0.2075   0.01004   0.00397  -0.0604   0.8691   0.6914
   0.000   0.2336   0.00997   0.00384  -0.0593   0.8458   0.6958
   0.250   0.2595   0.00993   0.00373  -0.0583   0.8192   0.7006
   0.500   0.2858   0.00993   0.00362  -0.0574   0.7879   0.7058
   0.750   0.3129   0.00995   0.00356  -0.0568   0.7567   0.7110
   1.000   0.3392   0.01000   0.00351  -0.0560   0.7169   0.7152
   1.250   0.3635   0.01024   0.00340  -0.0547   0.6254   0.7200
   1.500   0.3829   0.01125   0.00349  -0.0529   0.4340   0.7252
   1.750   0.4051   0.01218   0.00376  -0.0522   0.2901   0.7298
   2.000   0.4299   0.01276   0.00400  -0.0518   0.2165   0.7344
   2.250   0.4561   0.01316   0.00422  -0.0516   0.1800   0.7398
   2.500   0.4830   0.01348   0.00443  -0.0514   0.1604   0.7454
   2.750   0.5093   0.01375   0.00466  -0.0511   0.1480   0.7501
   3.000   0.5358   0.01405   0.00491  -0.0508   0.1383   0.7559
   3.250   0.5628   0.01431   0.00517  -0.0507   0.1309   0.7624
   3.500   0.5889   0.01459   0.00545  -0.0503   0.1244   0.7680
   3.750   0.6152   0.01490   0.00576  -0.0500   0.1190   0.7745
   4.000   0.6417   0.01516   0.00606  -0.0497   0.1137   0.7816
   4.250   0.6672   0.01551   0.00641  -0.0493   0.1087   0.7896
   4.500   0.6933   0.01581   0.00676  -0.0489   0.1042   0.7984
   4.750   0.7189   0.01606   0.00708  -0.0484   0.0992   0.8079
   5.000   0.7440   0.01643   0.00744  -0.0479   0.0943   0.8190
   5.250   0.7696   0.01663   0.00775  -0.0474   0.0890   0.8334
   5.500   0.7935   0.01689   0.00803  -0.0466   0.0842   0.8537
   5.750   0.8163   0.01703   0.00835  -0.0453   0.0794   0.8917
   6.000   0.8424   0.01725   0.00861  -0.0450   0.0750   1.0000
   6.250   0.8692   0.01766   0.00905  -0.0449   0.0703   1.0000
   6.500   0.8955   0.01808   0.00944  -0.0448   0.0662   1.0000
   6.750   0.9217   0.01854   0.00995  -0.0446   0.0619   1.0000
   7.000   0.9473   0.01902   0.01038  -0.0444   0.0584   1.0000
   7.250   0.9727   0.01956   0.01099  -0.0441   0.0546   1.0000
   7.500   0.9974   0.02015   0.01154  -0.0438   0.0520   1.0000
   7.750   1.0220   0.02081   0.01229  -0.0433   0.0491   1.0000
   8.000   1.0461   0.02145   0.01296  -0.0429   0.0468   1.0000
   8.250   1.0696   0.02221   0.01377  -0.0423   0.0447   1.0000
   8.500   1.0930   0.02295   0.01458  -0.0418   0.0426   1.0000
   8.750   1.1157   0.02371   0.01536  -0.0412   0.0411   1.0000
   9.000   1.1378   0.02463   0.01637  -0.0405   0.0397   1.0000
   9.250   1.1596   0.02558   0.01745  -0.0398   0.0385   1.0000
   9.500   1.1809   0.02652   0.01849  -0.0390   0.0374   1.0000
   9.750   1.2015   0.02747   0.01950  -0.0382   0.0365   1.0000
  10.000   1.2210   0.02853   0.02058  -0.0373   0.0358   1.0000
  10.250   1.2402   0.02977   0.02203  -0.0363   0.0350   1.0000
  10.500   1.2584   0.03102   0.02348  -0.0352   0.0341   1.0000
  10.750   1.2757   0.03226   0.02487  -0.0340   0.0333   1.0000
  11.000   1.2920   0.03347   0.02620  -0.0328   0.0327   1.0000
  11.250   1.3073   0.03471   0.02754  -0.0316   0.0321   1.0000
  11.500   1.3210   0.03604   0.02895  -0.0302   0.0317   1.0000
  11.750   1.3327   0.03759   0.03061  -0.0286   0.0314   1.0000
  12.000   1.3398   0.03959   0.03290  -0.0266   0.0310   1.0000
  12.250   1.3418   0.04165   0.03523  -0.0240   0.0307   1.0000
  12.500   1.3402   0.04392   0.03775  -0.0214   0.0304   1.0000
  12.750   1.3357   0.04648   0.04057  -0.0190   0.0301   1.0000
  13.000   1.3282   0.04942   0.04376  -0.0171   0.0299   1.0000
  13.250   1.3174   0.05287   0.04747  -0.0159   0.0297   1.0000
  13.500   1.3027   0.05703   0.05189  -0.0155   0.0296   1.0000
  13.750   1.2832   0.06225   0.05737  -0.0164   0.0295   1.0000
  14.000   1.2561   0.06935   0.06477  -0.0195   0.0294   1.0000
  14.250   1.2085   0.08209   0.07788  -0.0282   0.0296   1.0000
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