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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 100,000
Max Cl/Cd: 40.27 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hor04-il-100000-n5.txt
Download as CSV file: xf-hor04-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.6194   0.10478   0.09996   0.0240   1.0000   0.0339
  -7.750  -0.6151   0.10110   0.09632   0.0221   1.0000   0.0347
  -7.500  -0.6104   0.09738   0.09263   0.0196   1.0000   0.0356
  -7.250  -0.6021   0.09328   0.08855   0.0160   1.0000   0.0367
  -7.000  -0.5913   0.08895   0.08423   0.0114   1.0000   0.0379
  -6.750  -0.5770   0.08435   0.07961   0.0055   1.0000   0.0394
  -6.500  -0.5508   0.07918   0.07434  -0.0061   1.0000   0.0417
  -6.250  -0.5221   0.07436   0.06926  -0.0154   1.0000   0.0424
  -6.000  -0.4981   0.06987   0.06445  -0.0204   1.0000   0.0427
  -5.750  -0.4836   0.06330   0.05793  -0.0225   1.0000   0.0434
  -5.500  -0.4679   0.05859   0.05323  -0.0235   1.0000   0.0446
  -5.250  -0.4460   0.05440   0.04894  -0.0258   1.0000   0.0459
  -5.000  -0.4195   0.05016   0.04451  -0.0289   1.0000   0.0471
  -4.750  -0.3900   0.04590   0.03998  -0.0321   1.0000   0.0477
  -4.500  -0.3499   0.04002   0.03348  -0.0350   1.0000   0.0277
  -4.250  -0.3162   0.03596   0.02889  -0.0376   1.0000   0.0310
  -4.000  -0.2898   0.03319   0.02601  -0.0392   1.0000   0.0339
  -3.750  -0.2527   0.03084   0.02288  -0.0396   1.0000   0.0295
  -3.500  -0.2222   0.02730   0.01895  -0.0409   1.0000   0.0285
  -3.250  -0.1911   0.02475   0.01600  -0.0417   1.0000   0.0280
  -3.000  -0.1603   0.02261   0.01348  -0.0422   1.0000   0.0278
  -2.750  -0.1301   0.02079   0.01134  -0.0424   1.0000   0.0277
  -2.500  -0.1006   0.01920   0.00950  -0.0424   1.0000   0.0280
  -2.250  -0.0717   0.01785   0.00797  -0.0424   1.0000   0.0286
  -2.000  -0.0433   0.01673   0.00669  -0.0422   1.0000   0.0296
  -1.750  -0.0155   0.01546   0.00553  -0.0424   1.0000   0.0350
  -1.500   0.0127   0.01480   0.00480  -0.0424   1.0000   0.0429
  -1.250   0.0409   0.01396   0.00395  -0.0426   1.0000   0.0577
  -1.000   0.0696   0.01328   0.00325  -0.0427   1.0000   0.0751
  -0.750   0.0863   0.01037   0.00299  -0.0405   1.0000   0.7894
  -0.500   0.1105   0.00990   0.00253  -0.0392   1.0000   1.0000
  -0.250   0.1380   0.00994   0.00240  -0.0392   1.0000   1.0000
   0.000   0.1654   0.00999   0.00235  -0.0392   1.0000   1.0000
   0.250   0.1925   0.01005   0.00234  -0.0391   1.0000   1.0000
   0.500   0.2194   0.01013   0.00239  -0.0390   1.0000   1.0000
   0.750   0.2461   0.01022   0.00249  -0.0389   1.0000   1.0000
   1.000   0.2725   0.01034   0.00264  -0.0388   1.0000   1.0000
   1.250   0.2986   0.01048   0.00284  -0.0387   1.0000   1.0000
   1.500   0.3244   0.01065   0.00310  -0.0386   1.0000   1.0000
   1.750   0.3603   0.01079   0.00341  -0.0406   0.9890   1.0000
   2.000   0.4083   0.01084   0.00359  -0.0447   0.9503   1.0000
   2.250   0.4458   0.01107   0.00358  -0.0446   0.8051   1.0000
   2.500   0.4635   0.01174   0.00363  -0.0409   0.6457   1.0000
   2.750   0.4852   0.01269   0.00382  -0.0391   0.4681   1.0000
   3.000   0.5078   0.01475   0.00442  -0.0389   0.1534   1.0000
   3.250   0.5345   0.01593   0.00522  -0.0390   0.0889   1.0000
   3.500   0.5617   0.01682   0.00607  -0.0390   0.0735   1.0000
   3.750   0.5886   0.01762   0.00693  -0.0390   0.0621   1.0000
   4.000   0.6152   0.01859   0.00803  -0.0387   0.0568   1.0000
   4.250   0.6416   0.01974   0.00926  -0.0384   0.0520   1.0000
   4.500   0.6675   0.02123   0.01086  -0.0381   0.0468   1.0000
   4.750   0.6944   0.02243   0.01226  -0.0378   0.0405   1.0000
   5.000   0.7203   0.02445   0.01433  -0.0376   0.0359   1.0000
   5.250   0.7476   0.02587   0.01616  -0.0372   0.0303   1.0000
   5.500   0.7740   0.02806   0.01865  -0.0369   0.0277   1.0000
   5.750   0.7986   0.03128   0.02221  -0.0367   0.0260   1.0000
   6.000   0.8236   0.03494   0.02653  -0.0362   0.0250   1.0000
   6.250   0.8479   0.03861   0.03108  -0.0356   0.0224   1.0000
   6.500   0.8690   0.04283   0.03591  -0.0353   0.0205   1.0000
   6.750   0.8868   0.04800   0.04167  -0.0352   0.0201   1.0000
   7.000   0.9011   0.05365   0.04782  -0.0354   0.0201   1.0000
   7.250   0.9118   0.05976   0.05436  -0.0361   0.0202   1.0000
   7.500   0.9185   0.06611   0.06105  -0.0374   0.0205   1.0000
   7.750   0.9216   0.07258   0.06778  -0.0394   0.0208   1.0000
   8.000   0.9213   0.07914   0.07453  -0.0422   0.0212   1.0000
   8.250   0.9182   0.08578   0.08128  -0.0461   0.0216   1.0000
   8.500   0.9122   0.09253   0.08809  -0.0513   0.0219   1.0000
   8.750   0.9056   0.09913   0.09465  -0.0570   0.0223   1.0000
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