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ONERA OA212 AIRFOIL (oa212-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: ONERA OA212 AIRFOIL (oa212-il)
Reynolds number: 500,000
Max Cl/Cd: 76.34 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-oa212-il-500000-n5.txt
Download as CSV file: xf-oa212-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA OA212 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -1.1587   0.05953   0.05642  -0.0113   0.9174   0.0177
 -14.000  -1.1977   0.04995   0.04649  -0.0175   0.9138   0.0176
 -13.750  -1.2170   0.04524   0.04152  -0.0177   0.9098   0.0177
 -13.500  -1.2296   0.04193   0.03797  -0.0160   0.9057   0.0178
 -13.250  -1.2397   0.03950   0.03532  -0.0129   0.9020   0.0178
 -13.000  -1.2391   0.03733   0.03291  -0.0107   0.8988   0.0179
 -12.750  -1.2336   0.03527   0.03069  -0.0090   0.8952   0.0181
 -12.500  -1.2237   0.03358   0.02886  -0.0074   0.8919   0.0182
 -12.250  -1.2106   0.03218   0.02733  -0.0061   0.8889   0.0184
 -12.000  -1.1957   0.03094   0.02596  -0.0047   0.8862   0.0186
 -11.750  -1.1782   0.02978   0.02469  -0.0038   0.8833   0.0188
 -11.500  -1.1588   0.02868   0.02347  -0.0031   0.8799   0.0190
 -11.250  -1.1390   0.02763   0.02229  -0.0023   0.8766   0.0192
 -11.000  -1.1189   0.02662   0.02115  -0.0015   0.8733   0.0195
 -10.750  -1.0984   0.02565   0.02004  -0.0006   0.8705   0.0198
 -10.500  -1.0770   0.02471   0.01896   0.0002   0.8678   0.0201
 -10.250  -1.0536   0.02378   0.01790   0.0006   0.8642   0.0204
 -10.000  -1.0302   0.02292   0.01689   0.0010   0.8605   0.0207
  -9.750  -1.0065   0.02212   0.01595   0.0015   0.8571   0.0210
  -9.500  -0.9831   0.02133   0.01504   0.0021   0.8541   0.0213
  -9.250  -0.9594   0.02061   0.01426   0.0027   0.8512   0.0217
  -9.000  -0.9332   0.02001   0.01362   0.0028   0.8472   0.0222
  -8.750  -0.9071   0.01946   0.01300   0.0029   0.8433   0.0226
  -8.500  -0.8813   0.01890   0.01237   0.0032   0.8397   0.0231
  -8.250  -0.8558   0.01834   0.01172   0.0036   0.8363   0.0236
  -8.000  -0.8297   0.01780   0.01108   0.0039   0.8329   0.0241
  -7.750  -0.8023   0.01729   0.01048   0.0039   0.8289   0.0246
  -7.500  -0.7756   0.01671   0.00986   0.0040   0.8247   0.0252
  -7.250  -0.7489   0.01624   0.00935   0.0042   0.8208   0.0258
  -7.000  -0.7222   0.01583   0.00888   0.0044   0.8173   0.0264
  -6.750  -0.6942   0.01543   0.00844   0.0044   0.8134   0.0272
  -6.500  -0.6661   0.01505   0.00801   0.0043   0.8089   0.0281
  -6.250  -0.6384   0.01467   0.00757   0.0044   0.8046   0.0289
  -6.000  -0.6110   0.01428   0.00716   0.0045   0.8007   0.0300
  -5.750  -0.5828   0.01395   0.00680   0.0044   0.7969   0.0310
  -5.500  -0.5541   0.01363   0.00645   0.0043   0.7923   0.0322
  -5.250  -0.5257   0.01332   0.00609   0.0042   0.7876   0.0333
  -5.000  -0.4976   0.01300   0.00576   0.0042   0.7835   0.0348
  -4.750  -0.4690   0.01274   0.00548   0.0041   0.7796   0.0365
  -4.500  -0.4398   0.01248   0.00520   0.0039   0.7748   0.0384
  -4.250  -0.4111   0.01221   0.00493   0.0038   0.7697   0.0405
  -4.000  -0.3826   0.01199   0.00466   0.0038   0.7642   0.0428
  -3.750  -0.3533   0.01174   0.00443   0.0035   0.7561   0.0454
  -3.500  -0.3245   0.01154   0.00419   0.0034   0.7477   0.0488
  -3.250  -0.2952   0.01133   0.00398   0.0032   0.7396   0.0524
  -3.000  -0.2660   0.01116   0.00378   0.0030   0.7310   0.0564
  -2.750  -0.2365   0.01097   0.00360   0.0028   0.7226   0.0611
  -2.500  -0.2070   0.01082   0.00343   0.0025   0.7147   0.0661
  -2.250  -0.1775   0.01066   0.00329   0.0022   0.7079   0.0718
  -2.000  -0.1477   0.01051   0.00315   0.0019   0.7006   0.0776
  -1.750  -0.1181   0.01039   0.00302   0.0016   0.6936   0.0843
  -1.500  -0.0882   0.01024   0.00291   0.0012   0.6855   0.0917
  -1.250  -0.0583   0.01014   0.00278   0.0008   0.6770   0.0997
  -1.000  -0.0283   0.01000   0.00269   0.0004   0.6689   0.1098
  -0.750   0.0016   0.00989   0.00259   0.0000   0.6594   0.1219
  -0.500   0.0317   0.00976   0.00251  -0.0004   0.6490   0.1371
  -0.250   0.0618   0.00964   0.00243  -0.0009   0.6384   0.1585
   0.000   0.0918   0.00947   0.00236  -0.0014   0.6268   0.1943
   0.250   0.1218   0.00920   0.00230  -0.0020   0.6137   0.2650
   0.500   0.1516   0.00880   0.00223  -0.0027   0.5985   0.3781
   0.750   0.1712   0.00726   0.00236  -0.0011   0.5841   0.8440
   1.000   0.1984   0.00740   0.00246  -0.0007   0.5669   0.8789
   1.250   0.2270   0.00756   0.00254  -0.0006   0.5447   0.8950
   1.500   0.2556   0.00775   0.00260  -0.0006   0.5187   0.9058
   1.750   0.2843   0.00797   0.00269  -0.0007   0.4908   0.9170
   2.000   0.3100   0.00820   0.00281   0.0000   0.4630   0.9278
   2.250   0.3351   0.00842   0.00291   0.0008   0.4367   0.9373
   2.500   0.3597   0.00861   0.00300   0.0017   0.4159   0.9476
   2.750   0.3827   0.00873   0.00306   0.0030   0.4001   0.9575
   3.000   0.4096   0.00885   0.00310   0.0033   0.3855   0.9626
   3.250   0.4396   0.00899   0.00317   0.0027   0.3725   0.9640
   3.500   0.4696   0.00913   0.00326   0.0021   0.3619   0.9654
   3.750   0.4995   0.00926   0.00334   0.0016   0.3516   0.9670
   4.000   0.5294   0.00941   0.00344   0.0010   0.3426   0.9683
   4.250   0.5594   0.00955   0.00355   0.0004   0.3339   0.9695
   4.500   0.5891   0.00971   0.00367  -0.0002   0.3261   0.9708
   5.000   0.6486   0.01001   0.00392  -0.0013   0.3110   0.9735
   5.250   0.6786   0.01014   0.00405  -0.0019   0.3039   0.9746
   5.500   0.7084   0.01032   0.00420  -0.0025   0.2962   0.9757
   5.750   0.7383   0.01047   0.00436  -0.0031   0.2891   0.9769
   6.000   0.7679   0.01067   0.00453  -0.0037   0.2803   0.9782
   6.250   0.7974   0.01086   0.00471  -0.0043   0.2697   0.9795
   6.500   0.8265   0.01113   0.00490  -0.0049   0.2525   0.9812
   6.750   0.8553   0.01141   0.00511  -0.0055   0.2358   0.9830
   7.000   0.8848   0.01169   0.00535  -0.0062   0.2223   0.9842
   7.250   0.9144   0.01200   0.00560  -0.0070   0.2077   0.9854
   7.500   0.9436   0.01236   0.00589  -0.0078   0.1906   0.9867
   7.750   0.9721   0.01280   0.00625  -0.0085   0.1709   0.9882
   8.000   0.9999   0.01332   0.00665  -0.0092   0.1484   0.9900
   8.250   1.0267   0.01395   0.00714  -0.0098   0.1235   0.9922
   8.750   1.0776   0.01537   0.00830  -0.0107   0.0786   1.0000
   9.000   1.1003   0.01606   0.00890  -0.0107   0.0630   1.0000
   9.250   1.1231   0.01673   0.00952  -0.0106   0.0519   1.0000
   9.500   1.1460   0.01737   0.01012  -0.0105   0.0445   1.0000
   9.750   1.1686   0.01800   0.01074  -0.0104   0.0394   1.0000
  10.000   1.1907   0.01865   0.01139  -0.0103   0.0355   1.0000
  10.250   1.2125   0.01929   0.01206  -0.0101   0.0327   1.0000
  10.750   1.2524   0.02075   0.01357  -0.0096   0.0284   1.0000
  11.000   1.2684   0.02155   0.01441  -0.0088   0.0268   1.0000
  11.250   1.2831   0.02246   0.01535  -0.0079   0.0257   1.0000
  11.500   1.2990   0.02332   0.01627  -0.0072   0.0247   1.0000
  11.750   1.3140   0.02429   0.01729  -0.0065   0.0237   1.0000
  12.000   1.3276   0.02537   0.01842  -0.0058   0.0228   1.0000
  12.250   1.3391   0.02665   0.01974  -0.0050   0.0220   1.0000
  12.500   1.3521   0.02783   0.02099  -0.0044   0.0213   1.0000
  12.750   1.3641   0.02912   0.02235  -0.0038   0.0207   1.0000
  13.000   1.3749   0.03053   0.02384  -0.0032   0.0200   1.0000
  13.250   1.3842   0.03212   0.02548  -0.0027   0.0195   1.0000
  13.500   1.3916   0.03392   0.02735  -0.0023   0.0190   1.0000
  13.750   1.3962   0.03605   0.02954  -0.0019   0.0186   1.0000
  14.000   1.4026   0.03805   0.03163  -0.0016   0.0182   1.0000
  14.250   1.4078   0.04022   0.03391  -0.0015   0.0179   1.0000
  14.500   1.4115   0.04263   0.03641  -0.0015   0.0176   1.0000
  14.750   1.4138   0.04524   0.03912  -0.0016   0.0173   1.0000
  15.000   1.4147   0.04810   0.04208  -0.0019   0.0170   1.0000
  15.250   1.4146   0.05121   0.04529  -0.0024   0.0167   1.0000
  15.500   1.4131   0.05460   0.04877  -0.0032   0.0165   1.0000
  15.750   1.4100   0.05832   0.05260  -0.0041   0.0163   1.0000
  16.000   1.4054   0.06239   0.05678  -0.0053   0.0161   1.0000
  16.250   1.3989   0.06683   0.06132  -0.0068   0.0159   1.0000
  16.500   1.3909   0.07161   0.06620  -0.0084   0.0158   1.0000
  16.750   1.3811   0.07676   0.07146  -0.0103   0.0156   1.0000
  17.000   1.3711   0.08200   0.07681  -0.0123   0.0155   1.0000
  17.250   1.3634   0.08693   0.08185  -0.0142   0.0153   1.0000
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