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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 50,000
Max Cl/Cd: 32.31 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor04-il-50000-n5.txt
Download as CSV file: xf-hor04-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6282   0.11605   0.10923   0.0254   1.0000   0.0788
  -8.250  -0.6284   0.11322   0.10648   0.0218   1.0000   0.0819
  -8.000  -0.6299   0.11082   0.10416   0.0149   1.0000   0.0832
  -7.750  -0.6215   0.10554   0.09893   0.0153   1.0000   0.0849
  -7.500  -0.6113   0.10113   0.09451   0.0167   1.0000   0.0888
  -7.250  -0.6034   0.09732   0.09072   0.0127   1.0000   0.0937
  -6.750  -0.5830   0.08869   0.08213   0.0056   1.0000   0.1019
  -6.500  -0.5651   0.08448   0.07780  -0.0072   1.0000   0.1112
  -6.250  -0.5558   0.08037   0.07368  -0.0031   1.0000   0.1217
  -6.000  -0.5364   0.07613   0.06930  -0.0122   1.0000   0.1383
  -5.500  -0.5103   0.06819   0.06146  -0.0103   1.0000   0.1711
  -5.250  -0.4925   0.06429   0.05751  -0.0129   1.0000   0.1958
  -4.750  -0.3939   0.04940   0.04133  -0.0320   1.0000   0.0643
  -4.500  -0.3579   0.04473   0.03607  -0.0353   1.0000   0.0534
  -4.250  -0.3274   0.04076   0.03174  -0.0375   1.0000   0.0502
  -4.000  -0.2942   0.03710   0.02755  -0.0395   1.0000   0.0474
  -3.750  -0.2602   0.03388   0.02369  -0.0409   1.0000   0.0452
  -3.500  -0.2270   0.03129   0.02038  -0.0418   1.0000   0.0439
  -3.250  -0.1961   0.02900   0.01764  -0.0422   1.0000   0.0436
  -3.000  -0.1669   0.02675   0.01513  -0.0427   1.0000   0.0453
  -2.750  -0.1382   0.02508   0.01326  -0.0429   1.0000   0.0503
  -2.500  -0.1094   0.02357   0.01142  -0.0425   1.0000   0.0540
  -2.250  -0.0815   0.02217   0.00975  -0.0418   1.0000   0.0559
  -2.000  -0.0546   0.02065   0.00811  -0.0412   1.0000   0.0600
  -1.750  -0.0266   0.01958   0.00694  -0.0412   1.0000   0.0740
  -1.500   0.0024   0.01857   0.00578  -0.0412   1.0000   0.0851
  -1.250   0.0319   0.01757   0.00481  -0.0415   1.0000   0.1113
  -1.000   0.0451   0.01377   0.00409  -0.0379   1.0000   1.0000
  -0.750   0.0730   0.01379   0.00361  -0.0377   1.0000   1.0000
  -0.500   0.1005   0.01381   0.00330  -0.0376   1.0000   1.0000
  -0.250   0.1277   0.01385   0.00312  -0.0375   1.0000   1.0000
   0.000   0.1547   0.01391   0.00303  -0.0375   1.0000   1.0000
   0.250   0.1814   0.01398   0.00301  -0.0374   1.0000   1.0000
   0.500   0.2078   0.01407   0.00306  -0.0372   1.0000   1.0000
   0.750   0.2340   0.01418   0.00317  -0.0371   1.0000   1.0000
   1.000   0.2598   0.01431   0.00333  -0.0369   1.0000   1.0000
   1.250   0.2853   0.01446   0.00355  -0.0368   1.0000   1.0000
   1.500   0.3105   0.01465   0.00384  -0.0366   1.0000   1.0000
   1.750   0.3353   0.01487   0.00421  -0.0364   1.0000   1.0000
   2.000   0.3598   0.01514   0.00472  -0.0362   1.0000   1.0000
   2.250   0.3839   0.01546   0.00525  -0.0361   1.0000   1.0000
   2.500   0.4077   0.01586   0.00590  -0.0361   1.0000   1.0000
   2.750   0.4633   0.01604   0.00652  -0.0420   0.9679   1.0000
   3.000   0.5205   0.01611   0.00622  -0.0423   0.6911   1.0000
   3.250   0.5361   0.01737   0.00648  -0.0379   0.4486   1.0000
   3.500   0.5553   0.02044   0.00754  -0.0374   0.1398   1.0000
   3.750   0.5816   0.02191   0.00892  -0.0372   0.1110   1.0000
   4.000   0.6082   0.02330   0.01041  -0.0369   0.0977   1.0000
   4.250   0.6343   0.02466   0.01188  -0.0366   0.0826   1.0000
   4.500   0.6599   0.02634   0.01361  -0.0359   0.0748   1.0000
   4.750   0.6872   0.02828   0.01598  -0.0349   0.0700   1.0000
   5.000   0.7143   0.03042   0.01834  -0.0343   0.0636   1.0000
   5.250   0.7411   0.03278   0.02112  -0.0339   0.0556   1.0000
   5.500   0.7682   0.03573   0.02456  -0.0334   0.0524   1.0000
   5.750   0.7927   0.03897   0.02806  -0.0333   0.0491   1.0000
   6.000   0.8174   0.04254   0.03248  -0.0330   0.0445   1.0000
   6.250   0.8397   0.04657   0.03717  -0.0329   0.0420   1.0000
   6.500   0.8594   0.05123   0.04245  -0.0329   0.0414   1.0000
   6.750   0.8760   0.05633   0.04822  -0.0332   0.0413   1.0000
   7.000   0.8890   0.06182   0.05422  -0.0340   0.0416   1.0000
   7.250   0.8984   0.06757   0.06039  -0.0351   0.0422   1.0000
   7.500   0.9042   0.07344   0.06658  -0.0367   0.0430   1.0000
   7.750   0.9069   0.07933   0.07269  -0.0387   0.0438   1.0000
   8.000   0.9071   0.08516   0.07868  -0.0411   0.0447   1.0000
   8.250   0.9056   0.09091   0.08452  -0.0438   0.0455   1.0000
   8.500   0.9032   0.09657   0.09023  -0.0467   0.0462   1.0000
   8.750   0.8993   0.10203   0.09569  -0.0495   0.0468   1.0000
   9.000   0.8975   0.10762   0.10125  -0.0526   0.0474   1.0000
   9.250   0.8973   0.11299   0.10660  -0.0548   0.0478   1.0000
   9.500   0.8979   0.11833   0.11193  -0.0566   0.0481   1.0000
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