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ONERA HOR12 AIRFOIL (hor12-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR12 AIRFOIL (hor12-il)
Reynolds number: 200,000
Max Cl/Cd: 76.52 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor12-il-200000.txt
Download as CSV file: xf-hor12-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR12 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3306   0.09781   0.09438  -0.0294   1.0005   0.0907
  -9.250  -0.4038   0.10337   0.09971  -0.0158   1.0005   0.0854
  -9.000  -0.5860   0.03950   0.03505  -0.0814   1.0005   0.0556
  -8.750  -0.5665   0.03304   0.02781  -0.0884   1.0005   0.0566
  -8.500  -0.5415   0.02920   0.02343  -0.0918   1.0005   0.0581
  -8.250  -0.5163   0.02730   0.02149  -0.0928   1.0005   0.0598
  -8.000  -0.4899   0.02581   0.01985  -0.0936   1.0005   0.0613
  -7.750  -0.4634   0.02428   0.01812  -0.0944   1.0005   0.0629
  -7.500  -0.4376   0.02296   0.01659  -0.0949   1.0005   0.0648
  -7.250  -0.4132   0.02193   0.01532  -0.0949   1.0005   0.0667
  -7.000  -0.3911   0.02058   0.01380  -0.0947   1.0005   0.0685
  -6.750  -0.3725   0.01973   0.01298  -0.0938   1.0005   0.0703
  -6.500  -0.3465   0.01911   0.01234  -0.0942   0.9986   0.0726
  -6.250  -0.3020   0.01826   0.01135  -0.0978   0.9937   0.0767
  -6.000  -0.2589   0.01710   0.01010  -0.1012   0.9876   0.0809
  -5.750  -0.2139   0.01631   0.00931  -0.1048   0.9825   0.0874
  -5.500  -0.1716   0.01549   0.00850  -0.1079   0.9737   0.0981
  -5.250  -0.1296   0.01492   0.00792  -0.1109   0.9645   0.1147
  -5.000  -0.0899   0.01452   0.00749  -0.1132   0.9538   0.1294
  -4.750  -0.0560   0.01423   0.00716  -0.1142   0.9395   0.1407
  -4.500  -0.0273   0.01404   0.00689  -0.1140   0.9210   0.1508
  -4.250  -0.0001   0.01389   0.00671  -0.1135   0.9034   0.1604
  -4.000   0.0265   0.01368   0.00647  -0.1128   0.8869   0.1698
  -3.750   0.0534   0.01358   0.00626  -0.1122   0.8711   0.1808
  -3.500   0.0805   0.01344   0.00610  -0.1117   0.8561   0.1918
  -3.250   0.1079   0.01329   0.00591  -0.1112   0.8417   0.2033
  -3.000   0.1356   0.01318   0.00575  -0.1108   0.8281   0.2169
  -2.750   0.1639   0.01307   0.00561  -0.1106   0.8140   0.2320
  -2.500   0.1925   0.01295   0.00546  -0.1105   0.8003   0.2480
  -2.250   0.2211   0.01283   0.00534  -0.1105   0.7872   0.2657
  -2.000   0.2497   0.01275   0.00525  -0.1103   0.7747   0.2855
  -1.750   0.2782   0.01271   0.00518  -0.1102   0.7630   0.3070
  -1.500   0.3073   0.01265   0.00517  -0.1102   0.7501   0.3294
  -1.250   0.3364   0.01263   0.00517  -0.1103   0.7380   0.3533
  -1.000   0.3653   0.01262   0.00518  -0.1102   0.7269   0.3772
  -0.750   0.3943   0.01265   0.00520  -0.1101   0.7156   0.4035
  -0.500   0.4234   0.01266   0.00527  -0.1102   0.7036   0.4293
  -0.250   0.4524   0.01272   0.00531  -0.1101   0.6925   0.4565
   0.000   0.4811   0.01276   0.00534  -0.1100   0.6821   0.4820
   0.250   0.5101   0.01275   0.00538  -0.1100   0.6701   0.5073
   0.500   0.5390   0.01276   0.00540  -0.1100   0.6592   0.5318
   0.750   0.5675   0.01275   0.00540  -0.1098   0.6492   0.5561
   1.000   0.5962   0.01271   0.00544  -0.1098   0.6373   0.5826
   1.250   0.6246   0.01266   0.00550  -0.1097   0.6266   0.6119
   1.500   0.6526   0.01262   0.00553  -0.1094   0.6168   0.6500
   1.750   0.6793   0.01243   0.00564  -0.1089   0.6053   0.7161
   2.000   0.6972   0.01186   0.00546  -0.1059   0.5957   0.9995
   2.250   0.7272   0.01204   0.00549  -0.1062   0.5855   0.9995
   2.500   0.7569   0.01221   0.00560  -0.1065   0.5741   0.9995
   2.750   0.7862   0.01241   0.00570  -0.1066   0.5639   0.9995
   3.000   0.8153   0.01260   0.00580  -0.1067   0.5537   0.9995
   3.250   0.8443   0.01279   0.00596  -0.1068   0.5425   0.9995
   3.500   0.8731   0.01300   0.00610  -0.1069   0.5322   0.9995
   3.750   0.9018   0.01321   0.00624  -0.1069   0.5217   0.9995
   4.000   0.9304   0.01342   0.00644  -0.1069   0.5106   0.9995
   4.250   0.9589   0.01367   0.00664  -0.1069   0.5008   0.9995
   4.500   0.9872   0.01391   0.00684  -0.1069   0.4906   0.9995
   4.750   1.0154   0.01416   0.00709  -0.1069   0.4798   0.9995
   5.000   1.0434   0.01444   0.00732  -0.1068   0.4696   0.9995
   5.250   1.0711   0.01467   0.00753  -0.1067   0.4580   0.9995
   5.500   1.0987   0.01490   0.00778  -0.1065   0.4458   0.9995
   5.750   1.1261   0.01515   0.00804  -0.1064   0.4341   0.9995
   6.000   1.1532   0.01543   0.00826  -0.1062   0.4224   0.9995
   6.250   1.1801   0.01568   0.00850  -0.1059   0.4096   0.9995
   6.500   1.2066   0.01592   0.00877  -0.1056   0.3954   0.9995
   6.750   1.2328   0.01618   0.00904  -0.1053   0.3805   0.9995
   7.000   1.2588   0.01647   0.00934  -0.1050   0.3659   0.9995
   7.250   1.2848   0.01679   0.00969  -0.1047   0.3526   0.9995
   7.500   1.3104   0.01715   0.01008  -0.1043   0.3396   0.9995
   7.750   1.3354   0.01752   0.01046  -0.1038   0.3252   0.9995
   8.000   1.3600   0.01793   0.01087  -0.1034   0.3099   0.9995
   8.250   1.3841   0.01836   0.01133  -0.1028   0.2935   0.9995
   8.500   1.4076   0.01884   0.01183  -0.1022   0.2759   0.9995
   8.750   1.4301   0.01939   0.01237  -0.1015   0.2571   0.9995
   9.000   1.4512   0.02005   0.01299  -0.1006   0.2364   0.9995
   9.250   1.4712   0.02081   0.01372  -0.0996   0.2114   0.9995
   9.500   1.4879   0.02184   0.01463  -0.0982   0.1814   0.9995
   9.750   1.4996   0.02328   0.01587  -0.0963   0.1456   0.9995
  10.000   1.5062   0.02508   0.01744  -0.0938   0.1147   0.9995
  10.250   1.5105   0.02687   0.01911  -0.0909   0.0977   0.9995
  10.500   1.5142   0.02850   0.02074  -0.0879   0.0886   0.9995
  10.750   1.5111   0.03033   0.02255  -0.0842   0.0831   0.9995
  11.000   1.5139   0.03204   0.02435  -0.0816   0.0787   0.9995
  11.250   1.5173   0.03386   0.02624  -0.0795   0.0748   0.9995
  11.500   1.5161   0.03621   0.02860  -0.0775   0.0718   0.9995
  11.750   1.5169   0.03857   0.03103  -0.0758   0.0693   0.9995
  12.000   1.5219   0.04064   0.03322  -0.0746   0.0669   0.9995
  12.250   1.5256   0.04292   0.03558  -0.0735   0.0646   0.9995
  12.500   1.5278   0.04538   0.03812  -0.0726   0.0626   0.9995
  12.750   1.5280   0.04808   0.04081  -0.0714   0.0607   0.9995
  13.000   1.5308   0.05053   0.04331  -0.0701   0.0590   0.9995
  13.250   1.5350   0.05294   0.04588  -0.0694   0.0576   0.9995
  13.500   1.5383   0.05545   0.04851  -0.0687   0.0559   0.9995
  13.750   1.5410   0.05805   0.05120  -0.0681   0.0543   0.9995
  14.000   1.5431   0.06069   0.05389  -0.0676   0.0527   0.9995
  14.250   1.5465   0.06314   0.05634  -0.0665   0.0510   0.9995
  14.500   1.5505   0.06565   0.05893  -0.0653   0.0495   0.9995
  14.750   1.5501   0.06875   0.06222  -0.0651   0.0484   0.9995
  15.000   1.5491   0.07196   0.06560  -0.0650   0.0471   0.9995
  15.250   1.5477   0.07525   0.06902  -0.0651   0.0458   0.9995
  15.500   1.5470   0.07847   0.07233  -0.0652   0.0445   0.9995
  15.750   1.5488   0.08130   0.07517  -0.0651   0.0432   0.9995
  16.000   1.5505   0.08423   0.07813  -0.0641   0.0415   0.9995
  16.250   1.5411   0.08893   0.08307  -0.0656   0.0407   0.9995
  16.500   1.5327   0.09367   0.08803  -0.0672   0.0398   0.9995
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