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RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RAE 5215 AIRFOIL (rae5215-il)
Reynolds number: 500,000
Max Cl/Cd: 67.4 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5215-il-500000.txt
Download as CSV file: xf-rae5215-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5755   0.11468   0.11219  -0.0023   1.0000   0.0227
 -10.500  -0.5769   0.10918   0.10670  -0.0054   1.0000   0.0235
 -10.250  -0.6053   0.09289   0.09045  -0.0182   1.0000   0.0242
 -10.000  -0.6019   0.09051   0.08808  -0.0181   1.0000   0.0244
  -9.750  -0.6000   0.08685   0.08444  -0.0197   1.0000   0.0245
  -9.500  -0.6013   0.08169   0.07930  -0.0231   1.0000   0.0246
  -9.250  -0.6225   0.06946   0.06702  -0.0351   1.0000   0.0246
  -9.000  -0.6462   0.06190   0.05933  -0.0428   1.0000   0.0246
  -8.750  -0.6490   0.05764   0.05496  -0.0456   1.0000   0.0248
  -8.500  -0.6465   0.05403   0.05125  -0.0471   1.0000   0.0250
  -8.250  -0.6950   0.03193   0.02747  -0.0496   1.0000   0.0175
  -8.000  -0.6808   0.02871   0.02401  -0.0490   1.0000   0.0173
  -7.750  -0.6654   0.02539   0.02031  -0.0482   1.0000   0.0171
  -7.500  -0.6478   0.02257   0.01704  -0.0472   1.0000   0.0173
  -7.250  -0.6289   0.02050   0.01461  -0.0461   1.0000   0.0178
  -7.000  -0.6096   0.01930   0.01339  -0.0450   1.0000   0.0183
  -6.750  -0.5903   0.01861   0.01268  -0.0438   1.0000   0.0188
  -6.500  -0.5710   0.01779   0.01175  -0.0425   1.0000   0.0196
  -6.250  -0.5425   0.01691   0.01063  -0.0428   0.9991   0.0206
  -6.000  -0.5095   0.01570   0.00943  -0.0443   0.9974   0.0217
  -5.750  -0.4747   0.01503   0.00873  -0.0460   0.9956   0.0229
  -5.500  -0.4392   0.01445   0.00801  -0.0476   0.9939   0.0241
  -5.250  -0.4062   0.01353   0.00717  -0.0491   0.9914   0.0257
  -5.000  -0.3712   0.01320   0.00678  -0.0507   0.9890   0.0278
  -4.750  -0.3364   0.01248   0.00612  -0.0525   0.9870   0.0299
  -4.500  -0.3001   0.01207   0.00568  -0.0544   0.9854   0.0320
  -4.250  -0.2647   0.01141   0.00506  -0.0562   0.9834   0.0339
  -4.000  -0.2302   0.01101   0.00466  -0.0577   0.9801   0.0360
  -3.750  -0.1946   0.01056   0.00423  -0.0595   0.9776   0.0386
  -3.500  -0.1589   0.01027   0.00394  -0.0612   0.9752   0.0420
  -3.250  -0.1230   0.00985   0.00356  -0.0629   0.9730   0.0461
  -3.000  -0.0920   0.00952   0.00327  -0.0636   0.9673   0.0532
  -2.750  -0.0589   0.00878   0.00287  -0.0649   0.9629   0.1262
  -2.500  -0.0283   0.00718   0.00243  -0.0667   0.9568   0.4339
  -2.250  -0.0004   0.00685   0.00243  -0.0665   0.9477   0.5401
  -2.000   0.0267   0.00680   0.00243  -0.0659   0.9383   0.5746
  -1.750   0.0539   0.00680   0.00244  -0.0653   0.9302   0.5976
  -1.500   0.0812   0.00683   0.00248  -0.0648   0.9217   0.6170
  -1.250   0.1071   0.00689   0.00251  -0.0638   0.9111   0.6365
  -1.000   0.1319   0.00696   0.00257  -0.0624   0.8951   0.6555
  -0.750   0.1570   0.00702   0.00261  -0.0612   0.8774   0.6699
  -0.500   0.1836   0.00704   0.00259  -0.0604   0.8604   0.6790
  -0.250   0.2111   0.00703   0.00255  -0.0600   0.8456   0.6839
   0.000   0.2392   0.00704   0.00252  -0.0597   0.8322   0.6887
   0.250   0.2673   0.00707   0.00247  -0.0594   0.8164   0.6931
   0.500   0.2949   0.00705   0.00243  -0.0590   0.7970   0.6973
   0.750   0.3225   0.00708   0.00241  -0.0587   0.7734   0.7016
   1.000   0.3500   0.00716   0.00238  -0.0582   0.7391   0.7063
   1.250   0.3757   0.00743   0.00233  -0.0575   0.6577   0.7107
   1.500   0.3954   0.00867   0.00254  -0.0561   0.4151   0.7148
   1.750   0.4182   0.00977   0.00286  -0.0556   0.2303   0.7193
   2.250   0.4722   0.01056   0.00322  -0.0554   0.1512   0.7286
   2.500   0.4996   0.01075   0.00338  -0.0553   0.1411   0.7331
   2.750   0.5272   0.01096   0.00358  -0.0551   0.1336   0.7378
   3.000   0.5550   0.01117   0.00376  -0.0551   0.1276   0.7429
   3.250   0.5819   0.01148   0.00404  -0.0549   0.1213   0.7478
   3.500   0.6096   0.01160   0.00422  -0.0547   0.1174   0.7531
   3.750   0.6371   0.01181   0.00441  -0.0546   0.1122   0.7587
   4.000   0.6639   0.01211   0.00470  -0.0544   0.1064   0.7644
   4.250   0.6915   0.01219   0.00483  -0.0543   0.1015   0.7706
   4.500   0.7183   0.01248   0.00508  -0.0541   0.0961   0.7776
   4.750   0.7455   0.01264   0.00530  -0.0539   0.0918   0.7843
   5.000   0.7728   0.01279   0.00547  -0.0538   0.0871   0.7924
   5.250   0.7992   0.01305   0.00575  -0.0535   0.0824   0.8013
   5.500   0.8263   0.01318   0.00593  -0.0533   0.0780   0.8126
   5.750   0.8520   0.01344   0.00622  -0.0529   0.0735   0.8262
   6.000   0.8781   0.01354   0.00642  -0.0524   0.0692   0.8449
   6.250   0.9012   0.01370   0.00669  -0.0514   0.0649   0.8809
   6.500   0.9247   0.01372   0.00683  -0.0503   0.0606   1.0000
   6.750   0.9515   0.01412   0.00720  -0.0502   0.0562   1.0000
   7.000   0.9772   0.01463   0.00764  -0.0500   0.0520   1.0000
   7.250   1.0037   0.01501   0.00805  -0.0498   0.0486   1.0000
   7.500   1.0283   0.01565   0.00866  -0.0493   0.0457   1.0000
   7.750   1.0539   0.01611   0.00916  -0.0490   0.0433   1.0000
   8.000   1.0784   0.01671   0.00974  -0.0485   0.0414   1.0000
   8.250   1.1022   0.01741   0.01047  -0.0479   0.0398   1.0000
   8.500   1.1270   0.01793   0.01105  -0.0475   0.0383   1.0000
   8.750   1.1510   0.01852   0.01165  -0.0469   0.0371   1.0000
   9.000   1.1731   0.01941   0.01252  -0.0462   0.0360   1.0000
   9.250   1.1960   0.02019   0.01338  -0.0455   0.0353   1.0000
   9.500   1.2191   0.02089   0.01417  -0.0448   0.0345   1.0000
   9.750   1.2416   0.02164   0.01500  -0.0441   0.0338   1.0000
  10.000   1.2637   0.02241   0.01583  -0.0433   0.0331   1.0000
  10.250   1.2851   0.02323   0.01669  -0.0425   0.0325   1.0000
  10.500   1.3055   0.02420   0.01769  -0.0416   0.0320   1.0000
  10.750   1.3234   0.02571   0.01925  -0.0404   0.0314   1.0000
  11.000   1.3434   0.02658   0.02028  -0.0394   0.0310   1.0000
  11.250   1.3622   0.02759   0.02144  -0.0383   0.0306   1.0000
  11.500   1.3798   0.02874   0.02273  -0.0371   0.0302   1.0000
  11.750   1.3962   0.02997   0.02409  -0.0357   0.0298   1.0000
  12.000   1.4112   0.03125   0.02551  -0.0342   0.0295   1.0000
  12.250   1.4249   0.03257   0.02697  -0.0327   0.0291   1.0000
  12.500   1.4370   0.03394   0.02847  -0.0309   0.0289   1.0000
  12.750   1.4472   0.03537   0.03002  -0.0291   0.0286   1.0000
  13.000   1.4534   0.03683   0.03159  -0.0266   0.0284   1.0000
  13.250   1.4569   0.03845   0.03332  -0.0240   0.0282   1.0000
  13.500   1.4584   0.04032   0.03531  -0.0215   0.0280   1.0000
  13.750   1.4571   0.04256   0.03768  -0.0192   0.0279   1.0000
  14.000   1.4517   0.04530   0.04058  -0.0171   0.0277   1.0000
  14.250   1.4414   0.04864   0.04412  -0.0152   0.0276   1.0000
  14.500   1.4266   0.05260   0.04830  -0.0140   0.0275   1.0000
  14.750   1.4111   0.05672   0.05263  -0.0136   0.0275   1.0000
  15.000   1.3930   0.06157   0.05771  -0.0144   0.0275   1.0000
  15.250   1.3714   0.06749   0.06385  -0.0164   0.0275   1.0000
  15.500   1.3456   0.07483   0.07141  -0.0202   0.0275   1.0000
  16.000   1.2769   0.09699   0.09409  -0.0363   0.0277   1.0000
  16.250   0.6735   0.17843   0.17629  -0.0654   0.0363   1.0000
  16.500   0.6820   0.18037   0.17825  -0.0654   0.0361   1.0000
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