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RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RAE 5215 AIRFOIL (rae5215-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.2 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5215-il-1000000.txt
Download as CSV file: xf-rae5215-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4561   0.11259   0.11090  -0.0124   1.0000   0.0154
 -11.250  -0.4565   0.10861   0.10693  -0.0136   1.0000   0.0156
 -11.000  -0.9500   0.03134   0.02789  -0.0515   1.0000   0.0099
 -10.750  -0.9406   0.02825   0.02449  -0.0516   1.0000   0.0099
 -10.500  -0.9274   0.02550   0.02143  -0.0516   1.0000   0.0099
 -10.250  -0.9110   0.02312   0.01879  -0.0514   1.0000   0.0099
 -10.000  -0.8923   0.02111   0.01655  -0.0512   1.0000   0.0100
  -9.750  -0.8712   0.01961   0.01489  -0.0510   1.0000   0.0101
  -9.500  -0.8484   0.01850   0.01368  -0.0508   1.0000   0.0103
  -9.250  -0.8248   0.01766   0.01275  -0.0505   1.0000   0.0104
  -9.000  -0.8009   0.01692   0.01195  -0.0502   1.0000   0.0106
  -8.750  -0.7771   0.01626   0.01123  -0.0498   1.0000   0.0108
  -8.500  -0.7535   0.01563   0.01054  -0.0493   1.0000   0.0110
  -8.250  -0.7302   0.01500   0.00985  -0.0486   1.0000   0.0113
  -8.000  -0.7074   0.01442   0.00920  -0.0479   1.0000   0.0117
  -7.750  -0.6852   0.01395   0.00865  -0.0470   1.0000   0.0120
  -7.500  -0.6614   0.01324   0.00790  -0.0465   0.9997   0.0126
  -7.250  -0.6278   0.01291   0.00759  -0.0479   0.9983   0.0132
  -7.000  -0.5941   0.01258   0.00722  -0.0493   0.9968   0.0140
  -6.750  -0.5599   0.01230   0.00688  -0.0508   0.9954   0.0147
  -6.500  -0.5261   0.01168   0.00626  -0.0523   0.9942   0.0156
  -6.250  -0.4929   0.01137   0.00596  -0.0536   0.9918   0.0164
  -6.000  -0.4589   0.01107   0.00562  -0.0550   0.9896   0.0173
  -5.750  -0.4252   0.01054   0.00508  -0.0564   0.9873   0.0183
  -5.500  -0.3913   0.01022   0.00477  -0.0578   0.9850   0.0193
  -5.250  -0.3598   0.00997   0.00449  -0.0586   0.9802   0.0204
  -5.000  -0.3284   0.00953   0.00405  -0.0594   0.9755   0.0216
  -4.750  -0.2982   0.00926   0.00378  -0.0599   0.9698   0.0228
  -4.500  -0.2696   0.00905   0.00355  -0.0600   0.9627   0.0239
  -4.250  -0.2417   0.00874   0.00323  -0.0599   0.9554   0.0250
  -4.000  -0.2142   0.00853   0.00301  -0.0597   0.9478   0.0264
  -3.750  -0.1865   0.00837   0.00283  -0.0595   0.9404   0.0277
  -3.500  -0.1589   0.00814   0.00260  -0.0593   0.9326   0.0298
  -3.250  -0.1312   0.00800   0.00244  -0.0591   0.9247   0.0319
  -3.000  -0.1038   0.00781   0.00226  -0.0588   0.9146   0.0349
  -2.750  -0.0757   0.00764   0.00209  -0.0587   0.9049   0.0402
  -2.500  -0.0478   0.00738   0.00191  -0.0586   0.8951   0.0666
  -2.250  -0.0186   0.00682   0.00171  -0.0591   0.8876   0.1649
  -2.000   0.0105   0.00593   0.00147  -0.0600   0.8803   0.3611
  -1.750   0.0390   0.00542   0.00136  -0.0603   0.8680   0.4914
  -1.500   0.0668   0.00532   0.00133  -0.0600   0.8499   0.5409
  -1.250   0.0950   0.00531   0.00130  -0.0598   0.8323   0.5665
  -1.000   0.1234   0.00533   0.00129  -0.0596   0.8166   0.5853
  -0.750   0.1520   0.00536   0.00131  -0.0595   0.8030   0.6044
  -0.500   0.1807   0.00541   0.00135  -0.0594   0.7884   0.6222
  -0.250   0.2092   0.00547   0.00139  -0.0593   0.7710   0.6360
   0.000   0.2376   0.00554   0.00142  -0.0592   0.7501   0.6464
   0.250   0.2661   0.00563   0.00142  -0.0591   0.7205   0.6511
   0.500   0.2936   0.00586   0.00142  -0.0588   0.6597   0.6549
   0.750   0.3182   0.00670   0.00156  -0.0583   0.4832   0.6585
   1.000   0.3431   0.00753   0.00176  -0.0581   0.3167   0.6625
   1.250   0.3694   0.00814   0.00194  -0.0580   0.2073   0.6664
   1.500   0.3968   0.00851   0.00207  -0.0579   0.1544   0.6704
   1.750   0.4249   0.00872   0.00218  -0.0579   0.1361   0.6740
   2.000   0.4532   0.00885   0.00228  -0.0579   0.1273   0.6781
   2.250   0.4815   0.00899   0.00240  -0.0579   0.1205   0.6822
   2.500   0.5098   0.00911   0.00251  -0.0578   0.1162   0.6862
   2.750   0.5380   0.00928   0.00264  -0.0578   0.1111   0.6901
   3.000   0.5661   0.00944   0.00279  -0.0578   0.1067   0.6938
   3.250   0.5944   0.00952   0.00290  -0.0578   0.1031   0.6981
   3.500   0.6224   0.00967   0.00302  -0.0577   0.0979   0.7023
   3.750   0.6504   0.00983   0.00317  -0.0577   0.0937   0.7066
   4.000   0.6786   0.00995   0.00328  -0.0577   0.0902   0.7106
   4.250   0.7063   0.01010   0.00343  -0.0576   0.0857   0.7153
   4.500   0.7342   0.01024   0.00358  -0.0575   0.0822   0.7201
   4.750   0.7620   0.01039   0.00373  -0.0574   0.0781   0.7251
   5.000   0.7896   0.01058   0.00390  -0.0573   0.0735   0.7303
   5.250   0.8172   0.01072   0.00405  -0.0573   0.0692   0.7360
   5.500   0.8446   0.01092   0.00424  -0.0571   0.0645   0.7419
   5.750   0.8718   0.01112   0.00443  -0.0570   0.0599   0.7480
   6.000   0.8989   0.01132   0.00466  -0.0568   0.0559   0.7556
   6.250   0.9256   0.01160   0.00492  -0.0566   0.0517   0.7637
   6.500   0.9524   0.01182   0.00517  -0.0564   0.0480   0.7735
   6.750   0.9789   0.01209   0.00547  -0.0561   0.0443   0.7846
   7.000   1.0047   0.01243   0.00583  -0.0558   0.0405   0.7989
   7.250   1.0309   0.01265   0.00614  -0.0555   0.0379   0.8198
   7.500   1.0552   0.01292   0.00654  -0.0548   0.0354   0.8621
   7.750   1.0766   0.01294   0.00678  -0.0532   0.0336   1.0000
   8.000   1.1023   0.01337   0.00719  -0.0529   0.0319   1.0000
   8.250   1.1281   0.01378   0.00761  -0.0526   0.0307   1.0000
   8.500   1.1540   0.01415   0.00801  -0.0523   0.0298   1.0000
   8.750   1.1794   0.01457   0.00843  -0.0519   0.0289   1.0000
   9.000   1.2039   0.01511   0.00899  -0.0515   0.0280   1.0000
   9.250   1.2281   0.01567   0.00959  -0.0509   0.0273   1.0000
   9.500   1.2529   0.01612   0.01008  -0.0505   0.0268   1.0000
   9.750   1.2773   0.01659   0.01060  -0.0500   0.0263   1.0000
  10.000   1.3014   0.01709   0.01113  -0.0494   0.0258   1.0000
  10.250   1.3252   0.01760   0.01168  -0.0489   0.0253   1.0000
  10.500   1.3481   0.01820   0.01231  -0.0482   0.0248   1.0000
  10.750   1.3694   0.01898   0.01313  -0.0473   0.0244   1.0000
  11.000   1.3885   0.02000   0.01422  -0.0462   0.0239   1.0000
  11.250   1.4106   0.02060   0.01489  -0.0454   0.0238   1.0000
  11.500   1.4320   0.02124   0.01560  -0.0445   0.0235   1.0000
  11.750   1.4526   0.02194   0.01638  -0.0436   0.0233   1.0000
  12.000   1.4724   0.02269   0.01721  -0.0425   0.0231   1.0000
  12.250   1.4913   0.02348   0.01807  -0.0414   0.0228   1.0000
  12.500   1.5094   0.02430   0.01898  -0.0402   0.0226   1.0000
  12.750   1.5265   0.02517   0.01992  -0.0388   0.0223   1.0000
  13.000   1.5424   0.02607   0.02090  -0.0373   0.0221   1.0000
  13.250   1.5569   0.02702   0.02193  -0.0357   0.0219   1.0000
  13.500   1.5693   0.02802   0.02300  -0.0338   0.0217   1.0000
  13.750   1.5774   0.02908   0.02414  -0.0313   0.0216   1.0000
  14.000   1.5830   0.03028   0.02542  -0.0286   0.0214   1.0000
  14.250   1.5869   0.03168   0.02691  -0.0260   0.0213   1.0000
  14.500   1.5885   0.03335   0.02868  -0.0235   0.0211   1.0000
  14.750   1.5870   0.03539   0.03083  -0.0211   0.0210   1.0000
  15.000   1.5817   0.03794   0.03352  -0.0189   0.0208   1.0000
  15.250   1.5724   0.04107   0.03680  -0.0171   0.0207   1.0000
  15.500   1.5685   0.04380   0.03967  -0.0160   0.0207   1.0000
  15.750   1.5660   0.04655   0.04256  -0.0155   0.0206   1.0000
  16.000   1.5604   0.04983   0.04598  -0.0153   0.0206   1.0000
  16.250   1.5526   0.05364   0.04994  -0.0158   0.0205   1.0000
  16.500   1.5424   0.05806   0.05451  -0.0170   0.0205   1.0000
  16.750   1.5286   0.06340   0.06000  -0.0190   0.0205   1.0000
  17.000   1.5112   0.06985   0.06662  -0.0223   0.0204   1.0000
  17.250   1.4893   0.07769   0.07464  -0.0269   0.0204   1.0000
  17.500   1.4622   0.08717   0.08430  -0.0328   0.0204   1.0000
  17.750   1.4285   0.09832   0.09565  -0.0398   0.0205   1.0000
  18.000   1.3875   0.11113   0.10864  -0.0476   0.0205   1.0000
  18.250   1.3396   0.12555   0.12324  -0.0564   0.0206   1.0000
  18.500   1.2757   0.14439   0.14231  -0.0683   0.0206   1.0000
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