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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 500,000
Max Cl/Cd: 61.23 at α=1.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor04-il-500000.txt
Download as CSV file: xf-hor04-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6434   0.10861   0.10642   0.0286   1.0000   0.0097
  -8.250  -0.6409   0.10429   0.10211   0.0280   1.0000   0.0100
  -8.000  -0.6364   0.10060   0.09843   0.0271   1.0000   0.0101
  -7.750  -0.6324   0.09700   0.09485   0.0256   1.0000   0.0103
  -7.500  -0.6268   0.09325   0.09111   0.0231   1.0000   0.0105
  -7.250  -0.6172   0.08912   0.08699   0.0193   1.0000   0.0107
  -7.000  -0.6053   0.08475   0.08262   0.0148   1.0000   0.0110
  -6.750  -0.5907   0.08013   0.07798   0.0095   1.0000   0.0113
  -6.500  -0.5732   0.07524   0.07307   0.0036   1.0000   0.0118
  -6.250  -0.5525   0.07011   0.06790  -0.0026   1.0000   0.0125
  -6.000  -0.5276   0.06471   0.06243  -0.0092   1.0000   0.0135
  -5.750  -0.4876   0.05984   0.05740  -0.0170   1.0000   0.0152
  -5.500  -0.4579   0.05530   0.05270  -0.0213   1.0000   0.0155
  -5.250  -0.4297   0.05072   0.04792  -0.0248   1.0000   0.0156
  -5.000  -0.4009   0.04639   0.04337  -0.0277   1.0000   0.0156
  -4.750  -0.3764   0.03733   0.03403  -0.0329   1.0000   0.0167
  -4.500  -0.3494   0.03417   0.03073  -0.0347   1.0000   0.0174
  -4.250  -0.3206   0.03128   0.02766  -0.0363   1.0000   0.0182
  -4.000  -0.2904   0.02850   0.02466  -0.0378   1.0000   0.0193
  -3.750  -0.2589   0.02587   0.02178  -0.0389   1.0000   0.0209
  -3.500  -0.2266   0.02409   0.01972  -0.0393   1.0000   0.0238
  -3.250  -0.1951   0.02394   0.01929  -0.0390   1.0000   0.0253
  -3.000  -0.1634   0.02167   0.01670  -0.0398   1.0000   0.0254
  -2.250  -0.0682   0.01311   0.00730  -0.0421   1.0000   0.0235
  -2.000  -0.0379   0.01135   0.00538  -0.0423   1.0000   0.0216
  -1.750  -0.0083   0.01019   0.00413  -0.0424   1.0000   0.0214
  -1.500   0.0212   0.00938   0.00328  -0.0426   1.0000   0.0230
  -1.250   0.0508   0.00868   0.00253  -0.0430   1.0000   0.0275
  -1.000   0.0796   0.00837   0.00225  -0.0432   1.0000   0.0367
  -0.750   0.1086   0.00798   0.00187  -0.0434   1.0000   0.0481
  -0.500   0.1375   0.00624   0.00162  -0.0447   1.0000   0.5361
  -0.250   0.1542   0.00478   0.00145  -0.0419   1.0000   1.0000
   0.000   0.1824   0.00482   0.00144  -0.0420   1.0000   1.0000
   0.250   0.2106   0.00486   0.00146  -0.0421   1.0000   1.0000
   0.500   0.2388   0.00492   0.00150  -0.0422   1.0000   1.0000
   0.750   0.2735   0.00498   0.00156  -0.0438   0.9907   1.0000
   1.000   0.3092   0.00515   0.00164  -0.0450   0.9213   1.0000
   1.250   0.3295   0.00542   0.00168  -0.0426   0.8488   1.0000
   1.500   0.3533   0.00577   0.00172  -0.0413   0.7717   1.0000
   1.750   0.3788   0.00625   0.00179  -0.0406   0.6711   1.0000
   2.000   0.4058   0.00672   0.00190  -0.0404   0.5895   1.0000
   2.250   0.4335   0.00714   0.00203  -0.0405   0.5047   1.0000
   2.500   0.4605   0.00844   0.00232  -0.0411   0.2534   1.0000
   2.750   0.4883   0.00975   0.00281  -0.0418   0.0673   1.0000
   3.000   0.5166   0.01016   0.00322  -0.0420   0.0539   1.0000
   3.250   0.5448   0.01070   0.00375  -0.0421   0.0456   1.0000
   3.500   0.5729   0.01116   0.00427  -0.0422   0.0425   1.0000
   3.750   0.6009   0.01157   0.00472  -0.0422   0.0384   1.0000
   4.000   0.6283   0.01262   0.00580  -0.0423   0.0324   1.0000
   4.250   0.6561   0.01282   0.00609  -0.0423   0.0298   1.0000
   4.500   0.6839   0.01325   0.00657  -0.0423   0.0258   1.0000
   4.750   0.7105   0.01468   0.00809  -0.0422   0.0208   1.0000
   5.000   0.7384   0.01491   0.00838  -0.0421   0.0178   1.0000
   5.250   0.7656   0.01563   0.00917  -0.0420   0.0156   1.0000
   5.500   0.7913   0.01853   0.01235  -0.0417   0.0135   1.0000
   5.750   0.8176   0.02156   0.01584  -0.0412   0.0129   1.0000
   6.000   0.8419   0.02628   0.02117  -0.0407   0.0130   1.0000
   6.250   0.8663   0.02935   0.02465  -0.0401   0.0126   1.0000
   6.500   0.8887   0.03356   0.02934  -0.0395   0.0120   1.0000
   6.750   0.9022   0.04138   0.03778  -0.0389   0.0127   1.0000
  14.000   0.7245   0.17461   0.17260  -0.0732   0.0131   1.0000
  14.250   0.7257   0.17760   0.17559  -0.0744   0.0130   1.0000
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