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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 200,000
Max Cl/Cd: 46.2 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor04-il-200000-n5.txt
Download as CSV file: xf-hor04-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ONERA HOR04 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5125   0.10004   0.09674   0.0118   1.0000   0.0181
  -7.000  -0.5115   0.07156   0.06841  -0.0002   1.0000   0.0192
  -6.750  -0.5059   0.06707   0.06392  -0.0008   1.0000   0.0198
  -6.250  -0.4863   0.05698   0.05374  -0.0083   1.0000   0.0205
  -6.000  -0.4724   0.05171   0.04842  -0.0126   1.0000   0.0209
  -5.750  -0.4556   0.04638   0.04300  -0.0169   1.0000   0.0214
  -5.500  -0.4360   0.04110   0.03760  -0.0211   1.0000   0.0218
  -5.250  -0.4139   0.03604   0.03237  -0.0250   1.0000   0.0222
  -5.000  -0.3893   0.03111   0.02723  -0.0285   1.0000   0.0223
  -4.750  -0.3612   0.02604   0.02184  -0.0319   1.0000   0.0212
  -4.500  -0.3476   0.03636   0.03140  -0.0348   1.0000   0.0166
  -4.250  -0.3161   0.03220   0.02690  -0.0370   1.0000   0.0159
  -4.000  -0.2836   0.02850   0.02280  -0.0386   1.0000   0.0154
  -3.750  -0.2508   0.02523   0.01909  -0.0398   1.0000   0.0155
  -3.500  -0.2188   0.02289   0.01631  -0.0404   1.0000   0.0168
  -3.000  -0.1572   0.01957   0.01232  -0.0412   1.0000   0.0181
  -2.750  -0.1267   0.01753   0.00997  -0.0417   1.0000   0.0179
  -2.500  -0.0970   0.01594   0.00815  -0.0419   1.0000   0.0179
  -2.250  -0.0678   0.01465   0.00670  -0.0421   1.0000   0.0180
  -2.000  -0.0390   0.01359   0.00555  -0.0422   1.0000   0.0182
  -1.750  -0.0100   0.01234   0.00425  -0.0424   1.0000   0.0191
  -1.500   0.0190   0.01151   0.00341  -0.0428   1.0000   0.0217
  -1.250   0.0479   0.01103   0.00288  -0.0430   1.0000   0.0277
  -1.000   0.0762   0.01075   0.00265  -0.0432   1.0000   0.0429
  -0.750   0.1049   0.01030   0.00222  -0.0434   1.0000   0.0636
  -0.500   0.1309   0.00832   0.00216  -0.0441   1.0000   0.6194
  -0.250   0.1457   0.00718   0.00188  -0.0405   1.0000   1.0000
   0.000   0.1735   0.00723   0.00185  -0.0405   1.0000   1.0000
   0.250   0.2011   0.00728   0.00186  -0.0405   1.0000   1.0000
   0.500   0.2285   0.00735   0.00191  -0.0405   1.0000   1.0000
   0.750   0.2590   0.00744   0.00200  -0.0412   0.9952   1.0000
   1.000   0.2988   0.00751   0.00207  -0.0438   0.9721   1.0000
   1.250   0.3351   0.00760   0.00216  -0.0454   0.9363   1.0000
   1.500   0.3622   0.00784   0.00224  -0.0443   0.8480   1.0000
   1.750   0.3807   0.00837   0.00230  -0.0411   0.7230   1.0000
   2.000   0.4035   0.00909   0.00236  -0.0397   0.5929   1.0000
   2.250   0.4295   0.00975   0.00250  -0.0394   0.4618   1.0000
   2.500   0.4556   0.01089   0.00278  -0.0397   0.2639   1.0000
   2.750   0.4825   0.01207   0.00323  -0.0402   0.0972   1.0000
   3.000   0.5103   0.01270   0.00373  -0.0404   0.0642   1.0000
   3.250   0.5383   0.01315   0.00419  -0.0405   0.0530   1.0000
   3.500   0.5660   0.01372   0.00479  -0.0406   0.0472   1.0000
   3.750   0.5938   0.01426   0.00542  -0.0406   0.0432   1.0000
   4.000   0.6212   0.01494   0.00616  -0.0406   0.0395   1.0000
   4.250   0.6481   0.01579   0.00705  -0.0406   0.0350   1.0000
   4.500   0.6753   0.01640   0.00783  -0.0405   0.0303   1.0000
   4.750   0.7018   0.01732   0.00876  -0.0405   0.0253   1.0000
   5.000   0.7288   0.01838   0.01002  -0.0403   0.0221   1.0000
   5.250   0.7555   0.01972   0.01153  -0.0400   0.0193   1.0000
   5.500   0.7813   0.02107   0.01299  -0.0399   0.0166   1.0000
   5.750   0.8080   0.02253   0.01476  -0.0396   0.0147   1.0000
   6.000   0.8340   0.02512   0.01786  -0.0391   0.0133   1.0000
   6.250   0.8590   0.02846   0.02176  -0.0385   0.0124   1.0000
   6.500   0.8819   0.03284   0.02678  -0.0380   0.0118   1.0000
   6.750   0.9015   0.03857   0.03320  -0.0373   0.0116   1.0000
   7.000   0.9171   0.04532   0.04057  -0.0369   0.0117   1.0000
   7.250   0.9292   0.05208   0.04782  -0.0370   0.0117   1.0000
   7.500   0.9414   0.05655   0.05257  -0.0374   0.0110   1.0000
   7.750   0.9542   0.05823   0.05438  -0.0379   0.0100   1.0000
   8.000   0.8651   0.06162   0.05845  -0.0322   0.0118   1.0000
   8.250   0.8479   0.06875   0.06571  -0.0341   0.0121   1.0000
   8.500   0.8218   0.07612   0.07313  -0.0387   0.0128   1.0000
   8.750   0.8043   0.08353   0.08052  -0.0435   0.0131   1.0000
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