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ONERA OA213 AIRFOIL (oa213-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: ONERA OA213 AIRFOIL (oa213-il)
Reynolds number: 50,000
Max Cl/Cd: 26.52 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-oa213-il-50000.txt
Download as CSV file: xf-oa213-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4170   0.12463   0.11896  -0.0071   1.0000   0.1933
  -9.500  -0.3769   0.11740   0.11169  -0.0041   1.0000   0.2041
  -9.250  -0.4039   0.11715   0.11155  -0.0107   1.0000   0.2101
  -9.000  -0.3666   0.11072   0.10508  -0.0080   1.0000   0.2230
  -8.750  -0.3594   0.10693   0.10135  -0.0095   1.0000   0.2320
  -8.500  -0.3764   0.10569   0.10020  -0.0136   1.0000   0.2432
  -8.250  -0.3536   0.10107   0.09560  -0.0124   1.0000   0.2579
  -8.000  -0.3415   0.09743   0.09199  -0.0123   1.0000   0.2717
  -7.750  -0.3372   0.09451   0.08913  -0.0123   1.0000   0.2873
  -7.500  -0.3373   0.09210   0.08679  -0.0114   1.0000   0.3048
  -7.250  -0.3829   0.09277   0.08763  -0.0090   1.0000   0.3100
  -7.000  -0.3524   0.08874   0.08362  -0.0059   1.0000   0.3391
  -6.750  -0.3654   0.08750   0.08246  -0.0020   1.0000   0.3567
  -6.500  -0.4140   0.08805   0.08319   0.0029   1.0000   0.3599
  -6.250  -0.3760   0.08431   0.07944   0.0066   1.0000   0.4063
  -6.000  -0.4024   0.08386   0.07912   0.0122   1.0000   0.4262
  -5.750  -0.4099   0.08262   0.07797   0.0178   1.0000   0.4609
  -5.500  -0.3278   0.07762   0.07288   0.0202   1.0000   0.5576
  -4.500  -0.2369   0.06715   0.06248   0.0274   1.0000   0.7464
  -4.250  -0.3005   0.06727   0.06279   0.0342   1.0000   0.6980
  -4.000  -0.3602   0.06722   0.06291   0.0417   1.0000   0.6757
  -3.750  -0.4125   0.04960   0.04256  -0.0132   1.0000   0.1745
  -3.500  -0.3844   0.04562   0.03790  -0.0139   1.0000   0.1467
  -3.250  -0.3605   0.04317   0.03504  -0.0138   1.0000   0.1375
  -3.000  -0.3367   0.04100   0.03241  -0.0137   1.0000   0.1343
  -2.750  -0.3128   0.03921   0.03021  -0.0136   1.0000   0.1333
  -2.500  -0.2839   0.03753   0.02808  -0.0140   0.9986   0.1321
  -2.250  -0.2336   0.03608   0.02622  -0.0181   0.9895   0.1375
  -2.000  -0.1836   0.03493   0.02466  -0.0219   0.9797   0.1459
  -1.750  -0.1353   0.03408   0.02374  -0.0253   0.9690   0.1633
  -1.500  -0.0880   0.03350   0.02313  -0.0283   0.9576   0.1936
  -1.250   0.0069   0.02984   0.02261  -0.0347   0.9482   1.0000
  -1.000   0.0451   0.03076   0.02293  -0.0373   0.9327   1.0000
  -0.750   0.0860   0.03171   0.02348  -0.0405   0.9160   1.0000
  -0.500   0.1340   0.03273   0.02414  -0.0446   0.8986   1.0000
  -0.250   0.1621   0.03349   0.02467  -0.0453   0.8802   1.0000
   0.000   0.1944   0.03424   0.02521  -0.0465   0.8613   1.0000
   0.250   0.2347   0.03494   0.02572  -0.0487   0.8422   1.0000
   0.500   0.2852   0.03553   0.02613  -0.0523   0.8232   1.0000
   0.750   0.3230   0.03597   0.02642  -0.0535   0.8042   1.0000
   1.000   0.3419   0.03640   0.02675  -0.0519   0.7838   1.0000
   1.250   0.3705   0.03666   0.02691  -0.0514   0.7639   1.0000
   1.500   0.4039   0.03668   0.02684  -0.0511   0.7447   1.0000
   1.750   0.4378   0.03644   0.02653  -0.0504   0.7265   1.0000
   2.000   0.4704   0.03598   0.02598  -0.0491   0.7090   1.0000
   2.250   0.4856   0.03614   0.02609  -0.0465   0.6864   1.0000
   2.500   0.5130   0.03561   0.02550  -0.0444   0.6675   1.0000
   2.750   0.5417   0.03477   0.02460  -0.0421   0.6497   1.0000
   3.000   0.5705   0.03380   0.02356  -0.0396   0.6325   1.0000
   3.250   0.5991   0.03276   0.02244  -0.0369   0.6154   1.0000
   3.500   0.6274   0.03166   0.02126  -0.0342   0.5983   1.0000
   3.750   0.6501   0.03133   0.02085  -0.0319   0.5771   1.0000
   4.000   0.6747   0.03087   0.02029  -0.0296   0.5570   1.0000
   4.250   0.7008   0.03031   0.01962  -0.0274   0.5381   1.0000
   4.500   0.7268   0.02996   0.01912  -0.0254   0.5199   1.0000
   4.750   0.7524   0.02982   0.01880  -0.0237   0.5022   1.0000
   5.000   0.7757   0.03021   0.01909  -0.0224   0.4838   1.0000
   5.250   0.7985   0.03086   0.01969  -0.0215   0.4666   1.0000
   5.500   0.8223   0.03145   0.02018  -0.0206   0.4512   1.0000
   5.750   0.8474   0.03195   0.02054  -0.0196   0.4373   1.0000
   6.000   0.8691   0.03303   0.02164  -0.0191   0.4234   1.0000
   6.250   0.8887   0.03453   0.02325  -0.0189   0.4109   1.0000
   6.500   0.9095   0.03589   0.02464  -0.0184   0.4000   1.0000
   6.750   0.9373   0.03641   0.02501  -0.0177   0.3904   1.0000
   7.000   0.9497   0.03879   0.02766  -0.0177   0.3800   1.0000
   7.250   0.9734   0.04005   0.02889  -0.0173   0.3726   1.0000
   7.500   0.9795   0.04318   0.03233  -0.0172   0.3647   1.0000
   7.750   1.0119   0.04361   0.03260  -0.0167   0.3582   1.0000
   8.000   0.9916   0.04933   0.03882  -0.0167   0.3517   1.0000
   8.250   1.0052   0.05156   0.04115  -0.0163   0.3456   1.0000
   8.500   1.0151   0.05446   0.04414  -0.0161   0.3411   1.0000
   8.750   0.7430   0.09506   0.08484  -0.0324   0.3559   1.0000
   9.000   0.7520   0.09953   0.08937  -0.0337   0.3586   1.0000
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