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ONERA OA213 AIRFOIL (oa213-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: ONERA OA213 AIRFOIL (oa213-il)
Reynolds number: 100,000
Max Cl/Cd: 41.65 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oa213-il-100000.txt
Download as CSV file: xf-oa213-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3647   0.10170   0.09769  -0.0186   1.0000   0.0885
  -8.750  -0.3607   0.09799   0.09401  -0.0225   1.0000   0.0920
  -8.500  -0.3734   0.09438   0.09046  -0.0307   1.0000   0.0948
  -8.250  -0.2973   0.08747   0.08390  -0.0263   0.9989   0.1008
  -8.000  -0.2872   0.08282   0.07925  -0.0299   0.9947   0.1052
  -7.750  -0.2969   0.07762   0.07407  -0.0368   0.9887   0.1093
  -7.500  -0.3285   0.07255   0.06890  -0.0462   0.9788   0.1108
  -7.250  -0.4051   0.08009   0.07634  -0.0319   0.9911   0.1023
  -7.000  -0.4025   0.07596   0.07185  -0.0428   0.9811   0.1107
  -6.750  -0.3819   0.07002   0.06595  -0.0457   0.9766   0.1139
  -6.500  -0.3540   0.06646   0.06240  -0.0479   0.9721   0.1205
  -6.250  -0.2946   0.05076   0.04656  -0.0573   0.9437   0.1439
  -6.000  -0.3284   0.06021   0.05556  -0.0549   0.9557   0.1446
  -5.750  -0.2964   0.05625   0.05180  -0.0565   0.9517   0.1547
  -5.500  -0.2844   0.05357   0.04901  -0.0566   0.9428   0.1665
  -5.250  -0.2678   0.05111   0.04644  -0.0570   0.9351   0.1825
  -5.000  -0.2486   0.04881   0.04406  -0.0573   0.9276   0.2010
  -4.500  -0.1888   0.03741   0.03033  -0.0569   0.9127   0.0794
  -4.250  -0.1703   0.03506   0.02770  -0.0555   0.9035   0.0758
  -4.000  -0.1410   0.03314   0.02536  -0.0552   0.8973   0.0759
  -3.750  -0.1184   0.03154   0.02341  -0.0540   0.8883   0.0755
  -3.500  -0.0893   0.03003   0.02157  -0.0534   0.8815   0.0758
  -3.250  -0.0635   0.02904   0.02033  -0.0525   0.8729   0.0792
  -3.000  -0.0362   0.02790   0.01907  -0.0519   0.8655   0.0845
  -2.750  -0.0099   0.02706   0.01821  -0.0512   0.8570   0.0912
  -2.500   0.0148   0.02626   0.01745  -0.0502   0.8485   0.1018
  -2.250   0.0398   0.02544   0.01673  -0.0490   0.8402   0.1177
  -2.000   0.0609   0.02476   0.01616  -0.0474   0.8298   0.1443
  -1.500   0.2439   0.02145   0.01535  -0.0598   0.8185   1.0000
  -1.250   0.2607   0.02130   0.01504  -0.0575   0.8074   1.0000
  -1.000   0.2803   0.02125   0.01484  -0.0561   0.7952   1.0000
  -0.750   0.2972   0.02106   0.01451  -0.0536   0.7856   1.0000
  -0.500   0.3148   0.02084   0.01415  -0.0512   0.7753   1.0000
  -0.250   0.3344   0.02072   0.01393  -0.0497   0.7635   1.0000
   0.000   0.3490   0.02028   0.01334  -0.0460   0.7565   1.0000
   0.250   0.3698   0.02014   0.01313  -0.0447   0.7437   1.0000
   0.500   0.3893   0.01993   0.01283  -0.0429   0.7322   1.0000
   0.750   0.4051   0.01938   0.01215  -0.0393   0.7249   1.0000
   1.000   0.4257   0.01917   0.01187  -0.0378   0.7118   1.0000
   1.250   0.4455   0.01888   0.01150  -0.0358   0.6995   1.0000
   1.500   0.4641   0.01844   0.01097  -0.0332   0.6889   1.0000
   1.750   0.4828   0.01796   0.01039  -0.0305   0.6779   1.0000
   2.000   0.5034   0.01765   0.00999  -0.0286   0.6635   1.0000
   2.250   0.5240   0.01732   0.00958  -0.0266   0.6486   1.0000
   2.500   0.5449   0.01700   0.00917  -0.0247   0.6327   1.0000
   2.750   0.5660   0.01669   0.00874  -0.0227   0.6153   1.0000
   3.000   0.5878   0.01648   0.00840  -0.0210   0.5952   1.0000
   3.250   0.6105   0.01639   0.00820  -0.0197   0.5707   1.0000
   3.500   0.6331   0.01636   0.00800  -0.0184   0.5448   1.0000
   3.750   0.6559   0.01643   0.00783  -0.0171   0.5173   1.0000
   4.000   0.6795   0.01669   0.00788  -0.0164   0.4866   1.0000
   4.250   0.7032   0.01706   0.00805  -0.0158   0.4569   1.0000
   4.500   0.7270   0.01752   0.00830  -0.0153   0.4304   1.0000
   4.750   0.7509   0.01803   0.00857  -0.0148   0.4081   1.0000
   5.000   0.7750   0.01861   0.00893  -0.0144   0.3892   1.0000
   5.250   0.7994   0.01922   0.00941  -0.0142   0.3720   1.0000
   5.500   0.8238   0.01986   0.00988  -0.0139   0.3573   1.0000
   5.750   0.8485   0.02050   0.01042  -0.0137   0.3438   1.0000
   6.000   0.8734   0.02118   0.01109  -0.0136   0.3316   1.0000
   6.250   0.8983   0.02192   0.01175  -0.0134   0.3217   1.0000
   6.500   0.9236   0.02262   0.01234  -0.0133   0.3124   1.0000
   6.750   0.9482   0.02340   0.01320  -0.0132   0.3033   1.0000
   7.000   0.9739   0.02416   0.01380  -0.0131   0.2957   1.0000
   7.250   0.9981   0.02501   0.01479  -0.0131   0.2880   1.0000
   7.500   1.0235   0.02581   0.01556  -0.0131   0.2817   1.0000
   7.750   1.0485   0.02681   0.01659  -0.0131   0.2762   1.0000
   8.000   1.0721   0.02774   0.01768  -0.0130   0.2702   1.0000
   8.250   1.0977   0.02862   0.01850  -0.0130   0.2651   1.0000
   8.500   1.1210   0.02977   0.01978  -0.0130   0.2602   1.0000
   8.750   1.1432   0.03085   0.02106  -0.0129   0.2551   1.0000
   9.000   1.1672   0.03188   0.02216  -0.0129   0.2511   1.0000
   9.250   1.1933   0.03315   0.02337  -0.0130   0.2478   1.0000
   9.500   1.2112   0.03469   0.02528  -0.0127   0.2445   1.0000
   9.750   1.2296   0.03627   0.02714  -0.0125   0.2412   1.0000
  10.000   1.2495   0.03775   0.02881  -0.0123   0.2382   1.0000
  10.250   1.2709   0.03912   0.03028  -0.0121   0.2353   1.0000
  10.500   1.2948   0.04060   0.03179  -0.0122   0.2327   1.0000
  10.750   1.3052   0.04289   0.03442  -0.0116   0.2304   1.0000
  11.000   1.3094   0.04554   0.03749  -0.0106   0.2282   1.0000
  11.250   1.3103   0.04849   0.04079  -0.0096   0.2264   1.0000
  11.500   1.3060   0.05173   0.04434  -0.0084   0.2248   1.0000
  11.750   1.2928   0.05550   0.04840  -0.0071   0.2233   1.0000
  12.000   1.2145   0.06411   0.05735  -0.0050   0.2235   1.0000
  12.250   1.3494   0.05658   0.04946  -0.0070   0.2156   1.0000
  12.500   1.3130   0.06183   0.05501  -0.0050   0.2155   1.0000
  12.750   1.2677   0.06886   0.06227  -0.0041   0.2162   1.0000
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