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ONERA OA213 AIRFOIL (oa213-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: ONERA OA213 AIRFOIL (oa213-il)
Reynolds number: 500,000
Max Cl/Cd: 75.82 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oa213-il-500000-n5.txt
Download as CSV file: xf-oa213-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5653   0.08574   0.08338   0.0186   0.7905   0.0081
  -8.250  -0.5820   0.07778   0.07539   0.0103   0.7865   0.0081
  -8.000  -0.5948   0.06914   0.06665   0.0043   0.7825   0.0081
  -7.750  -0.6005   0.06116   0.05849   0.0007   0.7788   0.0081
  -7.500  -0.6035   0.05265   0.04969  -0.0013   0.7756   0.0081
  -7.250  -0.6406   0.02792   0.02332   0.0005   0.7737   0.0087
  -7.000  -0.6231   0.02366   0.01841   0.0015   0.7702   0.0089
  -6.750  -0.5997   0.02138   0.01573   0.0020   0.7660   0.0092
  -6.500  -0.5746   0.01977   0.01382   0.0024   0.7620   0.0094
  -6.250  -0.5487   0.01855   0.01233   0.0027   0.7582   0.0097
  -6.000  -0.5217   0.01758   0.01116   0.0029   0.7544   0.0099
  -5.750  -0.4945   0.01663   0.01008   0.0030   0.7497   0.0102
  -5.500  -0.4671   0.01596   0.00934   0.0031   0.7452   0.0105
  -5.250  -0.4395   0.01542   0.00871   0.0032   0.7412   0.0108
  -5.000  -0.4111   0.01489   0.00813   0.0031   0.7364   0.0112
  -4.750  -0.3828   0.01436   0.00752   0.0031   0.7312   0.0116
  -4.500  -0.3547   0.01385   0.00692   0.0031   0.7265   0.0121
  -4.250  -0.3261   0.01342   0.00641   0.0031   0.7216   0.0126
  -4.000  -0.2975   0.01297   0.00595   0.0030   0.7158   0.0134
  -3.750  -0.2688   0.01266   0.00560   0.0029   0.7104   0.0142
  -3.500  -0.2398   0.01231   0.00520   0.0027   0.7047   0.0151
  -3.250  -0.2107   0.01196   0.00480   0.0026   0.6982   0.0159
  -3.000  -0.1818   0.01163   0.00443   0.0024   0.6905   0.0171
  -2.750  -0.1525   0.01137   0.00410   0.0022   0.6777   0.0185
  -2.500  -0.1230   0.01111   0.00379   0.0020   0.6630   0.0203
  -2.250  -0.0933   0.01091   0.00355   0.0017   0.6512   0.0230
  -2.000  -0.0636   0.01071   0.00332   0.0014   0.6404   0.0265
  -1.500  -0.0039   0.01036   0.00293   0.0006   0.6175   0.0385
  -1.250   0.0261   0.01021   0.00278   0.0002   0.6057   0.0498
  -1.000   0.0561   0.01007   0.00265  -0.0003   0.5932   0.0676
  -0.750   0.0862   0.00991   0.00254  -0.0008   0.5797   0.0950
  -0.250   0.1455   0.00923   0.00233  -0.0020   0.5511   0.2732
   0.000   0.1689   0.00753   0.00223  -0.0020   0.5367   0.7438
   0.250   0.1951   0.00744   0.00234  -0.0013   0.5199   0.8316
   0.500   0.2227   0.00751   0.00239  -0.0010   0.5026   0.8653
   0.750   0.2508   0.00762   0.00243  -0.0009   0.4831   0.8859
   1.000   0.2784   0.00776   0.00249  -0.0006   0.4598   0.9038
   1.250   0.3046   0.00793   0.00256  -0.0001   0.4349   0.9235
   1.500   0.3327   0.00811   0.00261  -0.0001   0.4088   0.9324
   1.750   0.3628   0.00835   0.00267  -0.0008   0.3793   0.9368
   2.000   0.3929   0.00861   0.00276  -0.0015   0.3517   0.9414
   2.250   0.4225   0.00885   0.00286  -0.0021   0.3284   0.9456
   3.000   0.5120   0.00947   0.00317  -0.0040   0.2806   0.9598
   3.250   0.5426   0.00968   0.00329  -0.0048   0.2675   0.9649
   3.750   0.6053   0.01010   0.00357  -0.0068   0.2467   0.9744
   4.000   0.6375   0.01029   0.00371  -0.0080   0.2381   0.9789
   4.250   0.6696   0.01051   0.00387  -0.0092   0.2297   0.9838
   4.500   0.7029   0.01074   0.00404  -0.0107   0.2211   0.9880
   4.750   0.7357   0.01097   0.00422  -0.0121   0.2140   0.9931
   5.000   0.7686   0.01118   0.00441  -0.0135   0.2077   0.9983
   5.500   0.8246   0.01164   0.00480  -0.0144   0.1974   1.0000
   5.750   0.8523   0.01188   0.00501  -0.0148   0.1925   1.0000
   6.000   0.8798   0.01217   0.00526  -0.0152   0.1874   1.0000
   6.250   0.9076   0.01240   0.00549  -0.0156   0.1834   1.0000
   6.500   0.9352   0.01266   0.00573  -0.0159   0.1788   1.0000
   6.750   0.9625   0.01296   0.00601  -0.0163   0.1744   1.0000
   7.000   0.9897   0.01325   0.00630  -0.0167   0.1711   1.0000
   7.250   1.0169   0.01351   0.00658  -0.0170   0.1680   1.0000
   7.500   1.0438   0.01381   0.00689  -0.0174   0.1647   1.0000
   7.750   1.0703   0.01415   0.00722  -0.0177   0.1615   1.0000
   8.000   1.0962   0.01454   0.00760  -0.0179   0.1583   1.0000
   8.250   1.1226   0.01483   0.00794  -0.0182   0.1562   1.0000
   8.500   1.1486   0.01515   0.00829  -0.0184   0.1536   1.0000
   8.750   1.1739   0.01553   0.00867  -0.0186   0.1495   1.0000
   9.000   1.1980   0.01601   0.00912  -0.0188   0.1446   1.0000
   9.250   1.2232   0.01634   0.00951  -0.0189   0.1419   1.0000
   9.500   1.2477   0.01674   0.00993  -0.0191   0.1388   1.0000
   9.750   1.2711   0.01721   0.01042  -0.0192   0.1348   1.0000
  10.000   1.2934   0.01778   0.01099  -0.0193   0.1313   1.0000
  10.250   1.3165   0.01822   0.01150  -0.0193   0.1291   1.0000
  10.500   1.3383   0.01873   0.01206  -0.0193   0.1263   1.0000
  10.750   1.3576   0.01931   0.01267  -0.0189   0.1232   1.0000
  11.000   1.3739   0.02004   0.01339  -0.0182   0.1190   1.0000
  11.250   1.3929   0.02061   0.01402  -0.0178   0.1158   1.0000
  11.500   1.4105   0.02131   0.01476  -0.0173   0.1114   1.0000
  11.750   1.4262   0.02216   0.01561  -0.0167   0.1069   1.0000
  12.000   1.4432   0.02292   0.01642  -0.0162   0.1019   1.0000
  12.250   1.4569   0.02395   0.01744  -0.0156   0.0947   1.0000
  12.500   1.4659   0.02538   0.01880  -0.0148   0.0786   1.0000
  12.750   1.4484   0.02912   0.02223  -0.0128   0.0362   1.0000
  13.000   1.4471   0.03158   0.02471  -0.0118   0.0272   1.0000
  13.250   1.4520   0.03355   0.02674  -0.0112   0.0240   1.0000
  13.500   1.4579   0.03546   0.02874  -0.0108   0.0223   1.0000
  13.750   1.4620   0.03761   0.03098  -0.0105   0.0210   1.0000
  14.000   1.4660   0.03980   0.03326  -0.0102   0.0201   1.0000
  14.250   1.4702   0.04204   0.03562  -0.0102   0.0194   1.0000
  14.500   1.4724   0.04455   0.03824  -0.0102   0.0188   1.0000
  14.750   1.4727   0.04738   0.04117  -0.0104   0.0182   1.0000
  15.000   1.4709   0.05060   0.04450  -0.0109   0.0177   1.0000
  15.250   1.4668   0.05420   0.04822  -0.0115   0.0172   1.0000
  15.500   1.4595   0.05838   0.05253  -0.0125   0.0168   1.0000
  15.750   1.4493   0.06311   0.05740  -0.0139   0.0164   1.0000
  16.000   1.4411   0.06769   0.06210  -0.0152   0.0162   1.0000
  16.250   1.4302   0.07280   0.06736  -0.0170   0.0161   1.0000
  16.500   1.4165   0.07851   0.07321  -0.0190   0.0159   1.0000
  16.750   1.3995   0.08485   0.07971  -0.0213   0.0158   1.0000
  17.000   1.3794   0.09185   0.08687  -0.0241   0.0157   1.0000
  17.250   1.3567   0.09947   0.09465  -0.0271   0.0157   1.0000
  17.500   1.3318   0.10754   0.10288  -0.0304   0.0157   1.0000
  17.750   1.3066   0.11585   0.11134  -0.0339   0.0157   1.0000
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