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HQ 2.5/8 AIRFOIL (hq258-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/8 AIRFOIL (hq258-il)
Reynolds number: 200,000
Max Cl/Cd: 73.95 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq258-il-200000-n5.txt
Download as CSV file: xf-hq258-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/8 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4014   0.09706   0.09356  -0.0305   1.0000   0.0162
  -8.500  -0.4065   0.09169   0.08825  -0.0318   1.0000   0.0167
  -8.250  -0.4067   0.08791   0.08452  -0.0329   1.0000   0.0168
  -8.000  -0.4075   0.08446   0.08112  -0.0340   1.0000   0.0169
  -7.750  -0.4106   0.08126   0.07799  -0.0346   1.0000   0.0170
  -7.500  -0.4153   0.07797   0.07477  -0.0357   1.0000   0.0170
  -7.250  -0.4158   0.07414   0.07100  -0.0385   1.0000   0.0169
  -7.000  -0.4153   0.07032   0.06719  -0.0413   1.0000   0.0168
  -6.750  -0.4136   0.06728   0.06414  -0.0422   1.0000   0.0165
  -6.500  -0.4149   0.06477   0.06165  -0.0402   0.9988   0.0144
  -6.250  -0.3916   0.05818   0.05493  -0.0484   0.9923   0.0126
  -6.000  -0.3631   0.05123   0.04777  -0.0565   0.9864   0.0111
  -5.750  -0.3328   0.04222   0.03833  -0.0634   0.9793   0.0092
  -5.500  -0.2991   0.03689   0.03262  -0.0668   0.9751   0.0083
  -5.000  -0.2385   0.02929   0.02425  -0.0713   0.9652   0.0079
  -4.750  -0.2057   0.02510   0.01949  -0.0735   0.9617   0.0078
  -4.500  -0.1758   0.02207   0.01595  -0.0744   0.9563   0.0079
  -4.250  -0.1447   0.01946   0.01287  -0.0751   0.9516   0.0080
  -4.000  -0.1127   0.01648   0.00940  -0.0760   0.9482   0.0089
  -3.750  -0.0838   0.01578   0.00861  -0.0765   0.9423   0.0120
  -3.500  -0.0529   0.01469   0.00730  -0.0769   0.9373   0.0143
  -3.250  -0.0217   0.01356   0.00601  -0.0775   0.9329   0.0158
  -3.000   0.0064   0.01259   0.00493  -0.0775   0.9261   0.0203
  -2.750   0.0381   0.01202   0.00431  -0.0783   0.9215   0.0392
  -2.500   0.0662   0.01155   0.00389  -0.0784   0.9144   0.0687
  -2.250   0.0956   0.01087   0.00353  -0.0791   0.9089   0.1562
  -2.000   0.1212   0.00986   0.00329  -0.0794   0.9018   0.3909
  -1.750   0.1472   0.00930   0.00323  -0.0790   0.8955   0.5702
  -1.500   0.1725   0.00912   0.00323  -0.0781   0.8879   0.6540
  -1.250   0.1983   0.00897   0.00321  -0.0772   0.8812   0.7201
  -1.000   0.2207   0.00885   0.00322  -0.0755   0.8722   0.7803
  -0.750   0.2463   0.00874   0.00311  -0.0746   0.8639   0.8087
  -0.500   0.2733   0.00867   0.00295  -0.0742   0.8550   0.8240
  -0.250   0.2994   0.00860   0.00286  -0.0736   0.8455   0.8407
   0.000   0.3259   0.00853   0.00277  -0.0730   0.8369   0.8600
   0.250   0.3533   0.00845   0.00269  -0.0726   0.8278   0.8849
   0.500   0.3847   0.00834   0.00259  -0.0731   0.8158   0.9217
   0.750   0.4218   0.00826   0.00245  -0.0749   0.8008   1.0000
   1.000   0.4488   0.00830   0.00240  -0.0746   0.7862   1.0000
   1.250   0.4760   0.00836   0.00240  -0.0744   0.7729   1.0000
   1.500   0.5030   0.00843   0.00243  -0.0742   0.7587   1.0000
   1.750   0.5298   0.00851   0.00245  -0.0740   0.7427   1.0000
   2.000   0.5565   0.00859   0.00248  -0.0736   0.7253   1.0000
   2.250   0.5832   0.00870   0.00252  -0.0733   0.7070   1.0000
   2.500   0.6096   0.00882   0.00260  -0.0729   0.6868   1.0000
   2.750   0.6358   0.00896   0.00272  -0.0725   0.6641   1.0000
   3.000   0.6615   0.00914   0.00282  -0.0720   0.6362   1.0000
   3.250   0.6867   0.00935   0.00294  -0.0714   0.6025   1.0000
   3.500   0.7114   0.00962   0.00310  -0.0707   0.5640   1.0000
   3.750   0.7353   0.00997   0.00329  -0.0699   0.5195   1.0000
   4.000   0.7584   0.01040   0.00353  -0.0691   0.4696   1.0000
   4.250   0.7810   0.01091   0.00391  -0.0682   0.4185   1.0000
   4.500   0.8032   0.01148   0.00428  -0.0674   0.3662   1.0000
   4.750   0.8233   0.01230   0.00473  -0.0663   0.2919   1.0000
   5.000   0.8432   0.01321   0.00523  -0.0654   0.2189   1.0000
   5.250   0.8668   0.01373   0.00569  -0.0648   0.1876   1.0000
   5.500   0.8869   0.01470   0.00627  -0.0639   0.1194   1.0000
   5.750   0.9055   0.01592   0.00705  -0.0629   0.0508   1.0000
   6.000   0.9242   0.01725   0.00811  -0.0616   0.0111   1.0000
   6.250   0.9467   0.01804   0.00913  -0.0606   0.0078   1.0000
   6.500   0.9682   0.01892   0.01015  -0.0597   0.0057   1.0000
   6.750   0.9889   0.01996   0.01139  -0.0585   0.0052   1.0000
   7.000   1.0073   0.02130   0.01297  -0.0571   0.0048   1.0000
   7.250   1.0234   0.02290   0.01479  -0.0554   0.0046   1.0000
   7.500   1.0399   0.02450   0.01653  -0.0537   0.0045   1.0000
   7.750   1.0567   0.02617   0.01838  -0.0522   0.0044   1.0000
   8.000   1.0734   0.02803   0.02043  -0.0506   0.0044   1.0000
   8.250   1.0899   0.03009   0.02270  -0.0491   0.0044   1.0000
   8.500   1.1054   0.03242   0.02530  -0.0476   0.0043   1.0000
   8.750   1.1189   0.03497   0.02814  -0.0458   0.0043   1.0000
   9.000   1.1293   0.03777   0.03128  -0.0439   0.0044   1.0000
   9.250   1.1359   0.04071   0.03457  -0.0417   0.0044   1.0000
   9.500   1.1382   0.04379   0.03808  -0.0392   0.0044   1.0000
   9.750   1.1341   0.04687   0.04148  -0.0362   0.0044   1.0000
  10.000   1.1254   0.04992   0.04480  -0.0331   0.0044   1.0000
  10.250   1.1136   0.05323   0.04837  -0.0305   0.0044   1.0000
  10.500   1.0998   0.05698   0.05235  -0.0288   0.0045   1.0000
  10.750   1.0844   0.06120   0.05680  -0.0282   0.0045   1.0000
  11.000   1.0710   0.06551   0.06134  -0.0286   0.0045   1.0000
  11.250   1.0545   0.07073   0.06677  -0.0302   0.0045   1.0000
  11.500   1.0411   0.07609   0.07231  -0.0328   0.0046   1.0000
  11.750   1.0266   0.08244   0.07882  -0.0366   0.0046   1.0000
  12.000   1.0150   0.08906   0.08559  -0.0411   0.0046   1.0000
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