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ONERA OA213 AIRFOIL (oa213-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: ONERA OA213 AIRFOIL (oa213-il)
Reynolds number: 200,000
Max Cl/Cd: 54.03 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oa213-il-200000.txt
Download as CSV file: xf-oa213-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA OA213 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4080   0.08998   0.08712  -0.0147   0.9107   0.0456
  -8.000  -0.4124   0.08400   0.08113  -0.0235   0.9034   0.0468
  -7.750  -0.4303   0.07811   0.07499  -0.0321   0.8961   0.0478
  -7.500  -0.4340   0.07241   0.06910  -0.0350   0.8899   0.0484
  -7.250  -0.4246   0.06942   0.06622  -0.0330   0.8853   0.0491
  -7.000  -0.4127   0.06667   0.06346  -0.0329   0.8799   0.0501
  -6.750  -0.4025   0.06374   0.06047  -0.0331   0.8741   0.0514
  -6.500  -0.3962   0.06080   0.05739  -0.0325   0.8693   0.0532
  -6.250  -0.3865   0.05577   0.05165  -0.0352   0.8626   0.0582
  -6.000  -0.3723   0.05227   0.04824  -0.0345   0.8575   0.0592
  -5.750  -0.3606   0.05006   0.04600  -0.0327   0.8534   0.0606
  -5.500  -0.3379   0.04743   0.04325  -0.0338   0.8466   0.0638
  -5.250  -0.3232   0.04423   0.03949  -0.0327   0.8414   0.0703
  -5.000  -0.3083   0.04184   0.03711  -0.0310   0.8376   0.0721
  -4.750  -0.2821   0.03966   0.03481  -0.0319   0.8304   0.0764
  -4.500  -0.2634   0.03720   0.03194  -0.0306   0.8253   0.0845
  -4.250  -0.2454   0.03530   0.02998  -0.0288   0.8217   0.0878
  -4.000  -0.2076   0.02599   0.01872  -0.0257   0.8157   0.0403
  -3.750  -0.1821   0.02428   0.01674  -0.0246   0.8103   0.0402
  -3.500  -0.1594   0.02234   0.01464  -0.0228   0.8065   0.0409
  -3.250  -0.1305   0.02116   0.01344  -0.0230   0.7997   0.0426
  -3.000  -0.1046   0.02046   0.01267  -0.0222   0.7940   0.0463
  -2.750  -0.0819   0.01938   0.01149  -0.0203   0.7900   0.0492
  -2.500  -0.0537   0.01854   0.01073  -0.0203   0.7822   0.0534
  -2.250  -0.0312   0.01766   0.00981  -0.0185   0.7759   0.0599
  -2.000  -0.0067   0.01699   0.00912  -0.0172   0.7681   0.0685
  -1.750   0.0165   0.01606   0.00826  -0.0157   0.7603   0.0839
  -1.500   0.0403   0.01520   0.00753  -0.0145   0.7537   0.1175
  -1.250   0.0540   0.01238   0.00693  -0.0127   0.7459   0.6257
  -1.000   0.0611   0.01196   0.00716  -0.0055   0.7410   0.8731
  -0.750   0.0823   0.01208   0.00728  -0.0022   0.7316   0.9289
  -0.500   0.1366   0.01220   0.00719  -0.0048   0.7255   0.9715
  -0.250   0.2385   0.01229   0.00705  -0.0184   0.7146   0.9987
   0.000   0.2654   0.01206   0.00667  -0.0181   0.7063   1.0000
   0.250   0.2906   0.01186   0.00636  -0.0177   0.6959   1.0000
   0.500   0.3162   0.01170   0.00610  -0.0174   0.6853   1.0000
   0.750   0.3403   0.01151   0.00578  -0.0167   0.6755   1.0000
   1.000   0.3661   0.01137   0.00555  -0.0164   0.6632   1.0000
   1.250   0.3918   0.01126   0.00536  -0.0161   0.6502   1.0000
   1.500   0.4171   0.01117   0.00517  -0.0157   0.6366   1.0000
   1.750   0.4425   0.01110   0.00500  -0.0153   0.6221   1.0000
   2.000   0.4679   0.01105   0.00485  -0.0150   0.6062   1.0000
   2.250   0.4934   0.01104   0.00473  -0.0147   0.5885   1.0000
   2.500   0.5189   0.01106   0.00464  -0.0143   0.5693   1.0000
   2.750   0.5443   0.01113   0.00457  -0.0140   0.5484   1.0000
   3.000   0.5702   0.01124   0.00456  -0.0139   0.5229   1.0000
   3.250   0.5958   0.01141   0.00459  -0.0138   0.4943   1.0000
   3.500   0.6215   0.01166   0.00466  -0.0138   0.4618   1.0000
   3.750   0.6470   0.01201   0.00479  -0.0138   0.4276   1.0000
   4.000   0.6721   0.01244   0.00500  -0.0139   0.3954   1.0000
   4.250   0.6969   0.01291   0.00527  -0.0139   0.3684   1.0000
   4.500   0.7217   0.01340   0.00557  -0.0139   0.3463   1.0000
   4.750   0.7465   0.01389   0.00590  -0.0139   0.3286   1.0000
   5.000   0.7717   0.01436   0.00626  -0.0140   0.3138   1.0000
   5.250   0.7970   0.01482   0.00663  -0.0140   0.3010   1.0000
   5.500   0.8223   0.01531   0.00702  -0.0140   0.2898   1.0000
   5.750   0.8472   0.01583   0.00741  -0.0140   0.2798   1.0000
   6.000   0.8730   0.01623   0.00784  -0.0141   0.2703   1.0000
   6.250   0.8978   0.01681   0.00828  -0.0141   0.2626   1.0000
   6.500   0.9236   0.01722   0.00872  -0.0142   0.2551   1.0000
   6.750   0.9484   0.01778   0.00919  -0.0141   0.2487   1.0000
   7.000   0.9738   0.01826   0.00972  -0.0141   0.2426   1.0000
   7.250   0.9989   0.01873   0.01018  -0.0141   0.2367   1.0000
   7.500   1.0235   0.01940   0.01075  -0.0141   0.2314   1.0000
   7.750   1.0485   0.01984   0.01130  -0.0141   0.2261   1.0000
   8.000   1.0732   0.02035   0.01182  -0.0141   0.2214   1.0000
   8.250   1.0980   0.02106   0.01244  -0.0140   0.2173   1.0000
   8.500   1.1225   0.02164   0.01313  -0.0139   0.2136   1.0000
   8.750   1.1468   0.02220   0.01378  -0.0139   0.2097   1.0000
   9.000   1.1712   0.02279   0.01440  -0.0138   0.2063   1.0000
   9.250   1.1961   0.02350   0.01508  -0.0138   0.2032   1.0000
   9.500   1.2206   0.02434   0.01597  -0.0137   0.2003   1.0000
   9.750   1.2433   0.02498   0.01678  -0.0136   0.1972   1.0000
  10.000   1.2657   0.02555   0.01744  -0.0134   0.1934   1.0000
  10.250   1.2885   0.02608   0.01796  -0.0133   0.1897   1.0000
  10.500   1.3114   0.02690   0.01878  -0.0132   0.1858   1.0000
  10.750   1.3297   0.02748   0.01957  -0.0127   0.1822   1.0000
  11.000   1.3493   0.02807   0.02027  -0.0124   0.1788   1.0000
  11.250   1.3701   0.02867   0.02091  -0.0121   0.1758   1.0000
  11.500   1.3942   0.02955   0.02171  -0.0121   0.1724   1.0000
  11.750   1.4070   0.03023   0.02266  -0.0112   0.1697   1.0000
  12.000   1.4210   0.03099   0.02360  -0.0105   0.1666   1.0000
  12.250   1.4338   0.03169   0.02439  -0.0095   0.1637   1.0000
  12.500   1.4484   0.03237   0.02511  -0.0087   0.1611   1.0000
  12.750   1.4656   0.03322   0.02596  -0.0081   0.1578   1.0000
  13.000   1.4680   0.03432   0.02731  -0.0066   0.1550   1.0000
  13.250   1.4742   0.03538   0.02854  -0.0056   0.1518   1.0000
  13.500   1.4819   0.03635   0.02960  -0.0049   0.1484   1.0000
  13.750   1.4934   0.03730   0.03049  -0.0043   0.1446   1.0000
  14.000   1.4938   0.03899   0.03249  -0.0036   0.1416   1.0000
  14.250   1.4952   0.04067   0.03436  -0.0032   0.1370   1.0000
  14.500   1.4982   0.04236   0.03607  -0.0031   0.1325   1.0000
  14.750   1.4989   0.04458   0.03854  -0.0032   0.1273   1.0000
  15.000   1.4985   0.04704   0.04111  -0.0037   0.1207   1.0000
  15.250   1.4991   0.04971   0.04397  -0.0043   0.1121   1.0000
  15.500   1.4976   0.05281   0.04718  -0.0051   0.1020   1.0000
  16.000   1.4712   0.06247   0.05683  -0.0079   0.0660   1.0000
  16.250   1.4451   0.06935   0.06369  -0.0101   0.0552   1.0000
  16.500   1.4204   0.07642   0.07084  -0.0127   0.0506   1.0000
  16.750   1.3961   0.08373   0.07828  -0.0155   0.0487   1.0000
  17.000   1.3710   0.09149   0.08621  -0.0187   0.0476   1.0000
  17.250   1.3445   0.09974   0.09463  -0.0223   0.0471   1.0000
  17.500   1.3167   0.10847   0.10354  -0.0261   0.0470   1.0000
  17.750   1.2883   0.11753   0.11278  -0.0303   0.0471   1.0000
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