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RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il)
Reynolds number: 50,000
Max Cl/Cd: 30.42 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rae5212-il-50000-n5.txt
Download as CSV file: xf-rae5212-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE(NPL) 5212 AIRFOIL                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4977   0.10840   0.10050  -0.0430   1.0000   0.0574
 -11.000  -0.4972   0.10425   0.09639  -0.0439   1.0000   0.0569
 -10.750  -0.4993   0.09969   0.09188  -0.0452   1.0000   0.0564
 -10.500  -0.5047   0.09450   0.08674  -0.0472   1.0000   0.0559
 -10.250  -0.5143   0.08883   0.08111  -0.0498   1.0000   0.0553
 -10.000  -0.5298   0.08307   0.07540  -0.0526   1.0000   0.0546
  -9.750  -0.5514   0.07761   0.06996  -0.0550   1.0000   0.0541
  -9.500  -0.5760   0.07315   0.06551  -0.0560   1.0000   0.0535
  -9.250  -0.6027   0.06966   0.06201  -0.0549   1.0000   0.0531
  -9.000  -0.6231   0.06613   0.05838  -0.0535   1.0000   0.0528
  -8.750  -0.6391   0.06269   0.05479  -0.0518   1.0000   0.0526
  -8.500  -0.6501   0.05939   0.05130  -0.0499   1.0000   0.0525
  -8.250  -0.6565   0.05624   0.04790  -0.0479   1.0000   0.0529
  -8.000  -0.6588   0.05326   0.04465  -0.0460   1.0000   0.0537
  -7.750  -0.6580   0.05035   0.04137  -0.0440   1.0000   0.0547
  -7.500  -0.6542   0.04750   0.03810  -0.0421   1.0000   0.0559
  -7.250  -0.6466   0.04478   0.03492  -0.0402   1.0000   0.0569
  -7.000  -0.6354   0.04225   0.03201  -0.0385   1.0000   0.0576
  -6.750  -0.6210   0.04004   0.02966  -0.0371   1.0000   0.0587
  -6.500  -0.6056   0.03829   0.02780  -0.0357   1.0000   0.0606
  -6.250  -0.5892   0.03669   0.02601  -0.0343   1.0000   0.0633
  -6.000  -0.5714   0.03506   0.02407  -0.0328   1.0000   0.0662
  -5.750  -0.5519   0.03355   0.02222  -0.0313   1.0000   0.0682
  -5.500  -0.5333   0.03217   0.02093  -0.0298   1.0000   0.0712
  -5.250  -0.5147   0.03114   0.01983  -0.0283   1.0000   0.0756
  -5.000  -0.4951   0.03019   0.01869  -0.0265   1.0000   0.0799
  -4.750  -0.4776   0.02920   0.01778  -0.0248   1.0000   0.0841
  -4.500  -0.4602   0.02840   0.01692  -0.0231   1.0000   0.0911
  -4.250  -0.4434   0.02753   0.01604  -0.0215   1.0000   0.0979
  -4.000  -0.4259   0.02675   0.01520  -0.0201   1.0000   0.1083
  -3.750  -0.4083   0.02585   0.01434  -0.0190   1.0000   0.1226
  -3.500  -0.3893   0.02473   0.01343  -0.0185   1.0000   0.1491
  -3.250  -0.3706   0.02276   0.01232  -0.0189   1.0000   0.2571
  -3.000  -0.3598   0.02228   0.01336  -0.0150   0.9984   0.5473
  -2.750  -0.3337   0.02309   0.01408  -0.0138   0.9921   0.6271
  -2.500  -0.3117   0.02392   0.01490  -0.0113   0.9855   0.6842
  -2.250  -0.2974   0.02466   0.01573  -0.0062   0.9788   0.7346
  -2.000  -0.2778   0.02506   0.01610  -0.0029   0.9728   0.7695
  -1.750  -0.2507   0.02501   0.01586  -0.0031   0.9664   0.7827
  -1.500  -0.2188   0.02501   0.01566  -0.0043   0.9608   0.7913
  -1.250  -0.1894   0.02495   0.01543  -0.0053   0.9545   0.7997
  -1.000  -0.1583   0.02496   0.01530  -0.0064   0.9483   0.8077
  -0.750  -0.1271   0.02497   0.01517  -0.0077   0.9423   0.8158
  -0.500  -0.0979   0.02497   0.01507  -0.0085   0.9355   0.8237
  -0.250  -0.0628   0.02506   0.01506  -0.0105   0.9300   0.8317
   0.000  -0.0370   0.02505   0.01499  -0.0107   0.9221   0.8399
   0.250  -0.0015   0.02515   0.01504  -0.0127   0.9163   0.8482
   0.500   0.0251   0.02518   0.01504  -0.0130   0.9081   0.8572
   0.750   0.0610   0.02529   0.01514  -0.0150   0.9017   0.8660
   1.000   0.0892   0.02535   0.01521  -0.0156   0.8930   0.8764
   1.250   0.1281   0.02544   0.01533  -0.0180   0.8860   0.8859
   1.500   0.1589   0.02552   0.01547  -0.0191   0.8762   0.8976
   1.750   0.2027   0.02560   0.01560  -0.0223   0.8691   0.9091
   2.000   0.2379   0.02570   0.01580  -0.0243   0.8583   0.9232
   2.250   0.2854   0.02574   0.01593  -0.0282   0.8493   0.9377
   2.500   0.3334   0.02567   0.01598  -0.0321   0.8380   0.9556
   2.750   0.3787   0.02546   0.01590  -0.0354   0.8237   0.9896
   3.000   0.4156   0.02519   0.01571  -0.0369   0.8084   1.0000
   3.250   0.4553   0.02471   0.01531  -0.0383   0.7913   1.0000
   3.500   0.5007   0.02378   0.01448  -0.0398   0.7689   1.0000
   3.750   0.5387   0.02275   0.01351  -0.0396   0.7378   1.0000
   4.000   0.5636   0.02215   0.01293  -0.0377   0.7000   1.0000
   4.250   0.5912   0.02164   0.01239  -0.0364   0.6558   1.0000
   4.500   0.6137   0.02144   0.01215  -0.0346   0.5992   1.0000
   4.750   0.6456   0.02122   0.01156  -0.0338   0.5070   1.0000
   5.000   0.6660   0.02192   0.01145  -0.0318   0.3937   1.0000
   5.250   0.6770   0.02318   0.01207  -0.0294   0.3076   1.0000
   5.500   0.6893   0.02449   0.01289  -0.0274   0.2520   1.0000
   5.750   0.7051   0.02569   0.01379  -0.0260   0.2181   1.0000
   6.000   0.7237   0.02680   0.01472  -0.0250   0.1964   1.0000
   6.250   0.7443   0.02787   0.01568  -0.0242   0.1805   1.0000
   6.500   0.7670   0.02890   0.01662  -0.0237   0.1681   1.0000
   6.750   0.7916   0.02996   0.01756  -0.0235   0.1586   1.0000
   7.000   0.8218   0.03097   0.01870  -0.0239   0.1509   1.0000
   7.250   0.8521   0.03213   0.01975  -0.0245   0.1447   1.0000
   7.500   0.8822   0.03326   0.02104  -0.0249   0.1382   1.0000
   7.750   0.9107   0.03446   0.02229  -0.0252   0.1326   1.0000
   8.000   0.9424   0.03594   0.02371  -0.0261   0.1288   1.0000
   8.250   0.9691   0.03745   0.02551  -0.0261   0.1249   1.0000
   8.500   0.9935   0.03896   0.02723  -0.0259   0.1208   1.0000
   8.750   1.0172   0.04047   0.02880  -0.0257   0.1171   1.0000
   9.000   1.0428   0.04237   0.03072  -0.0259   0.1145   1.0000
   9.250   1.0602   0.04446   0.03324  -0.0248   0.1123   1.0000
   9.500   1.0750   0.04663   0.03580  -0.0235   0.1097   1.0000
   9.750   1.0885   0.04874   0.03820  -0.0222   0.1070   1.0000
  10.000   1.1020   0.05078   0.04043  -0.0210   0.1044   1.0000
  10.250   1.1160   0.05302   0.04283  -0.0199   0.1025   1.0000
  10.500   1.1299   0.05561   0.04558  -0.0190   0.1011   1.0000
  10.750   1.1282   0.05866   0.04902  -0.0166   0.1000   1.0000
  11.000   1.1174   0.06190   0.05269  -0.0135   0.0989   1.0000
  11.250   1.1009   0.06520   0.05634  -0.0101   0.0980   1.0000
  11.500   1.0792   0.06878   0.06020  -0.0071   0.0972   1.0000
  11.750   1.0532   0.07297   0.06465  -0.0050   0.0967   1.0000
  12.000   1.0220   0.07816   0.07006  -0.0044   0.0966   1.0000
  12.250   0.9833   0.08503   0.07711  -0.0059   0.0968   1.0000
  12.500   0.9370   0.09462   0.08684  -0.0106   0.0975   1.0000
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