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ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: ONERA HOR04 AIRFOIL (hor04-il)
Reynolds number: 50,000
Max Cl/Cd: 28.09 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hor04-il-50000.txt
Download as CSV file: xf-hor04-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6374   0.11806   0.11134   0.0282   1.0000   0.1369
  -8.250  -0.6343   0.11486   0.10818   0.0268   1.0000   0.1442
  -8.000  -0.6436   0.11364   0.10708   0.0204   1.0000   0.1467
  -7.750  -0.6266   0.10756   0.10098   0.0243   1.0000   0.1573
  -7.500  -0.6248   0.10401   0.09750   0.0210   1.0000   0.1629
  -7.250  -0.6194   0.10083   0.09436   0.0170   1.0000   0.1735
  -7.000  -0.6086   0.09627   0.08983   0.0182   1.0000   0.1849
  -6.750  -0.6004   0.09242   0.08600   0.0162   1.0000   0.1987
  -6.500  -0.5929   0.08915   0.08275   0.0089   1.0000   0.2153
  -6.250  -0.5817   0.08471   0.07830   0.0149   1.0000   0.2372
  -6.000  -0.5720   0.08104   0.07467   0.0148   1.0000   0.2629
  -5.500  -0.5523   0.07416   0.06788   0.0166   1.0000   0.3283
  -5.250  -0.5428   0.07095   0.06473   0.0203   1.0000   0.3701
  -5.000  -0.5352   0.06806   0.06190   0.0251   1.0000   0.4227
  -4.750  -0.5261   0.06501   0.05892   0.0335   1.0000   0.4821
  -4.250  -0.3057   0.04550   0.03882   0.0386   1.0000   0.9694
  -4.000  -0.3114   0.04382   0.03723   0.0409   1.0000   0.9516
  -3.750  -0.3398   0.04348   0.03704   0.0473   1.0000   0.9164
  -3.500  -0.2507   0.03428   0.02475  -0.0432   1.0000   0.1583
  -3.250  -0.2138   0.03122   0.02109  -0.0446   1.0000   0.1435
  -3.000  -0.1770   0.02893   0.01802  -0.0454   1.0000   0.1328
  -2.750  -0.1454   0.02630   0.01514  -0.0456   1.0000   0.1267
  -2.500  -0.1133   0.02433   0.01272  -0.0453   1.0000   0.1225
  -2.250  -0.0839   0.02258   0.01073  -0.0447   1.0000   0.1232
  -2.000  -0.0561   0.02109   0.00907  -0.0439   1.0000   0.1357
  -1.750  -0.0279   0.01974   0.00760  -0.0430   1.0000   0.1476
  -1.500   0.0007   0.01835   0.00626  -0.0426   1.0000   0.1676
  -1.250   0.0279   0.01530   0.00522  -0.0430   1.0000   0.5052
  -1.000   0.0455   0.01377   0.00405  -0.0379   1.0000   1.0000
  -0.750   0.0734   0.01379   0.00360  -0.0377   1.0000   1.0000
  -0.500   0.1009   0.01381   0.00330  -0.0377   1.0000   1.0000
  -0.250   0.1281   0.01386   0.00313  -0.0376   1.0000   1.0000
   0.000   0.1550   0.01391   0.00304  -0.0375   1.0000   1.0000
   0.250   0.1817   0.01398   0.00302  -0.0374   1.0000   1.0000
   0.500   0.2081   0.01407   0.00307  -0.0373   1.0000   1.0000
   0.750   0.2343   0.01418   0.00318  -0.0372   1.0000   1.0000
   1.000   0.2601   0.01431   0.00334  -0.0370   1.0000   1.0000
   1.250   0.2856   0.01447   0.00357  -0.0368   1.0000   1.0000
   1.500   0.3107   0.01465   0.00386  -0.0366   1.0000   1.0000
   1.750   0.3355   0.01488   0.00423  -0.0365   1.0000   1.0000
   2.000   0.3600   0.01515   0.00473  -0.0363   1.0000   1.0000
   2.250   0.3842   0.01547   0.00527  -0.0362   1.0000   1.0000
   2.500   0.4079   0.01587   0.00592  -0.0362   1.0000   1.0000
   2.750   0.4311   0.01637   0.00670  -0.0364   1.0000   1.0000
   3.000   0.4542   0.01700   0.00766  -0.0368   1.0000   1.0000
   3.250   0.4767   0.01779   0.00882  -0.0374   1.0000   1.0000
   3.500   0.5604   0.01995   0.00835  -0.0361   0.2555   1.0000
   3.750   0.5858   0.02219   0.01004  -0.0355   0.1888   1.0000
   4.000   0.6138   0.02412   0.01190  -0.0345   0.1664   1.0000
   4.250   0.6423   0.02629   0.01404  -0.0336   0.1519   1.0000
   4.500   0.6706   0.02853   0.01641  -0.0330   0.1359   1.0000
   4.750   0.7012   0.03118   0.01968  -0.0324   0.1309   1.0000
   5.000   0.7312   0.03436   0.02337  -0.0319   0.1282   1.0000
   5.250   0.7586   0.03776   0.02725  -0.0317   0.1202   1.0000
   5.500   0.7865   0.04202   0.03210  -0.0315   0.1223   1.0000
   5.750   0.8151   0.04719   0.03826  -0.0318   0.1340   1.0000
   6.000   0.8422   0.05328   0.04495  -0.0325   0.1518   1.0000
   6.750   0.8443   0.09049   0.08439  -0.0943   0.4584   1.0000
   7.000   0.8513   0.09442   0.08830  -0.0923   0.4307   1.0000
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