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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 200,000
Max Cl/Cd: 67.49 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2010-il-200000-n5.txt
Download as CSV file: xf-hq2010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/10 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4714   0.08902   0.08549  -0.0314   1.0000   0.0124
  -9.500  -0.4771   0.08352   0.08004  -0.0342   1.0000   0.0122
  -9.250  -0.4849   0.07768   0.07426  -0.0375   1.0000   0.0120
  -9.000  -0.4969   0.07079   0.06745  -0.0420   1.0000   0.0117
  -8.750  -0.5217   0.06141   0.05810  -0.0499   1.0000   0.0114
  -8.500  -0.5584   0.05207   0.04857  -0.0533   1.0000   0.0108
  -8.250  -0.5813   0.04506   0.04127  -0.0527   1.0000   0.0106
  -8.000  -0.5940   0.04011   0.03598  -0.0506   1.0000   0.0105
  -7.750  -0.5902   0.03518   0.03057  -0.0506   0.9966   0.0106
  -7.500  -0.5668   0.03091   0.02576  -0.0530   0.9895   0.0109
  -7.250  -0.5390   0.02755   0.02189  -0.0551   0.9844   0.0113
  -7.000  -0.5119   0.02496   0.01888  -0.0562   0.9781   0.0119
  -6.750  -0.4812   0.02279   0.01632  -0.0577   0.9737   0.0128
  -6.500  -0.4502   0.02142   0.01464  -0.0588   0.9687   0.0144
  -6.250  -0.4214   0.01962   0.01258  -0.0595   0.9628   0.0155
  -6.000  -0.3899   0.01823   0.01102  -0.0607   0.9585   0.0167
  -5.750  -0.3614   0.01726   0.00994  -0.0611   0.9517   0.0181
  -5.500  -0.3306   0.01630   0.00885  -0.0619   0.9462   0.0202
  -5.250  -0.3012   0.01546   0.00790  -0.0625   0.9401   0.0235
  -5.000  -0.2717   0.01484   0.00725  -0.0630   0.9335   0.0288
  -4.750  -0.2419   0.01411   0.00644  -0.0636   0.9277   0.0355
  -4.500  -0.2132   0.01369   0.00592  -0.0639   0.9203   0.0444
  -4.250  -0.1835   0.01327   0.00549  -0.0644   0.9137   0.0572
  -4.000  -0.1558   0.01283   0.00504  -0.0645   0.9058   0.0708
  -3.750  -0.1278   0.01238   0.00461  -0.0646   0.8989   0.0878
  -3.500  -0.1010   0.01193   0.00425  -0.0645   0.8915   0.1205
  -3.250  -0.0746   0.01138   0.00393  -0.0646   0.8848   0.1901
  -3.000  -0.0491   0.01083   0.00365  -0.0644   0.8775   0.2759
  -2.750  -0.0248   0.01014   0.00347  -0.0641   0.8711   0.4171
  -2.500  -0.0003   0.00978   0.00346  -0.0634   0.8641   0.5259
  -2.250   0.0259   0.00965   0.00343  -0.0628   0.8580   0.5875
  -2.000   0.0519   0.00960   0.00342  -0.0622   0.8506   0.6266
  -1.750   0.0785   0.00957   0.00341  -0.0617   0.8445   0.6623
  -1.500   0.1045   0.00956   0.00343  -0.0610   0.8371   0.6900
  -1.250   0.1312   0.00954   0.00339  -0.0605   0.8308   0.7095
  -1.000   0.1573   0.00953   0.00337  -0.0599   0.8222   0.7270
  -0.750   0.1837   0.00952   0.00335  -0.0593   0.8143   0.7451
  -0.500   0.2101   0.00950   0.00330  -0.0588   0.8056   0.7598
  -0.250   0.2364   0.00947   0.00325  -0.0583   0.7947   0.7700
   0.000   0.2629   0.00943   0.00317  -0.0577   0.7827   0.7796
   0.250   0.2895   0.00940   0.00310  -0.0573   0.7705   0.7900
   0.500   0.3159   0.00937   0.00305  -0.0567   0.7592   0.8002
   0.750   0.3423   0.00934   0.00300  -0.0562   0.7476   0.8107
   1.000   0.3685   0.00932   0.00297  -0.0557   0.7346   0.8221
   1.250   0.3948   0.00931   0.00296  -0.0551   0.7216   0.8344
   1.500   0.4212   0.00930   0.00297  -0.0547   0.7096   0.8478
   1.750   0.4474   0.00929   0.00298  -0.0541   0.6973   0.8625
   2.000   0.4741   0.00928   0.00300  -0.0537   0.6842   0.8801
   2.500   0.5351   0.00929   0.00307  -0.0544   0.6540   0.9303
   3.000   0.6012   0.00946   0.00321  -0.0567   0.6155   1.0000
   3.250   0.6268   0.00962   0.00330  -0.0563   0.5923   1.0000
   3.500   0.6521   0.00982   0.00341  -0.0558   0.5652   1.0000
   3.750   0.6767   0.01006   0.00354  -0.0551   0.5325   1.0000
   4.000   0.7005   0.01038   0.00373  -0.0544   0.4947   1.0000
   4.250   0.7231   0.01079   0.00394  -0.0535   0.4414   1.0000
   4.500   0.7443   0.01135   0.00422  -0.0525   0.3904   1.0000
   4.750   0.7658   0.01192   0.00457  -0.0516   0.3411   1.0000
   5.000   0.7873   0.01251   0.00493  -0.0507   0.2984   1.0000
   5.250   0.8099   0.01303   0.00535  -0.0500   0.2691   1.0000
   5.500   0.8334   0.01348   0.00574  -0.0495   0.2478   1.0000
   5.750   0.8569   0.01392   0.00614  -0.0489   0.2295   1.0000
   6.000   0.8805   0.01434   0.00655  -0.0483   0.2076   1.0000
   6.250   0.9034   0.01483   0.00698  -0.0477   0.1812   1.0000
   6.500   0.9257   0.01538   0.00747  -0.0470   0.1518   1.0000
   6.750   0.9463   0.01610   0.00802  -0.0462   0.1190   1.0000
   7.000   0.9660   0.01694   0.00868  -0.0452   0.0885   1.0000
   7.250   0.9858   0.01775   0.00938  -0.0442   0.0688   1.0000
   7.500   1.0067   0.01843   0.01006  -0.0434   0.0579   1.0000
   7.750   1.0278   0.01907   0.01076  -0.0425   0.0520   1.0000
   8.000   1.0484   0.01973   0.01149  -0.0416   0.0470   1.0000
   8.250   1.0683   0.02044   0.01228  -0.0406   0.0416   1.0000
   8.500   1.0882   0.02111   0.01296  -0.0397   0.0341   1.0000
   8.750   1.1082   0.02175   0.01368  -0.0388   0.0285   1.0000
   9.000   1.1266   0.02254   0.01450  -0.0376   0.0234   1.0000
   9.250   1.1447   0.02331   0.01536  -0.0364   0.0180   1.0000
   9.500   1.1600   0.02433   0.01642  -0.0349   0.0128   1.0000
   9.750   1.1735   0.02546   0.01761  -0.0332   0.0104   1.0000
  10.000   1.1847   0.02660   0.01888  -0.0311   0.0092   1.0000
  10.250   1.1945   0.02777   0.02024  -0.0288   0.0085   1.0000
  10.500   1.2028   0.02906   0.02168  -0.0265   0.0079   1.0000
  10.750   1.2101   0.03043   0.02320  -0.0244   0.0075   1.0000
  11.000   1.2161   0.03193   0.02484  -0.0223   0.0071   1.0000
  11.250   1.2201   0.03364   0.02669  -0.0203   0.0068   1.0000
  11.500   1.2207   0.03570   0.02890  -0.0184   0.0063   1.0000
  11.750   1.2239   0.03761   0.03100  -0.0168   0.0060   1.0000
  12.000   1.2252   0.03979   0.03335  -0.0155   0.0057   1.0000
  12.250   1.2258   0.04211   0.03586  -0.0144   0.0055   1.0000
  12.500   1.2242   0.04477   0.03870  -0.0136   0.0054   1.0000
  12.750   1.2212   0.04773   0.04185  -0.0131   0.0053   1.0000
  13.000   1.2172   0.05096   0.04525  -0.0130   0.0050   1.0000
  13.250   1.2102   0.05476   0.04924  -0.0134   0.0049   1.0000
  13.500   1.2028   0.05883   0.05351  -0.0142   0.0050   1.0000
  13.750   1.1930   0.06352   0.05840  -0.0157   0.0049   1.0000
  14.000   1.1820   0.06873   0.06380  -0.0177   0.0049   1.0000
  14.250   1.1691   0.07461   0.06987  -0.0205   0.0048   1.0000
  14.500   1.1551   0.08113   0.07659  -0.0238   0.0049   1.0000
  14.750   1.1394   0.08852   0.08417  -0.0279   0.0049   1.0000
  15.000   1.1230   0.09647   0.09232  -0.0325   0.0049   1.0000
  15.250   1.1036   0.10552   0.10156  -0.0378   0.0049   1.0000
  15.500   1.0846   0.11493   0.11113  -0.0433   0.0050   1.0000
  15.750   1.0637   0.12501   0.12138  -0.0491   0.0051   1.0000
  16.000   1.0411   0.13605   0.13256  -0.0554   0.0052   1.0000
  16.250   1.0169   0.14812   0.14476  -0.0622   0.0054   1.0000
  16.500   0.9902   0.16174   0.15849  -0.0695   0.0058   1.0000
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