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HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il)
Reynolds number: 200,000
Max Cl/Cd: 55.84 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1010-il-200000-n5.txt
Download as CSV file: xf-hq1010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/10 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6979   0.05698   0.05340  -0.0397   1.0000   0.0091
 -10.000  -0.7233   0.05114   0.04738  -0.0428   1.0000   0.0091
  -9.750  -0.7514   0.04615   0.04211  -0.0420   1.0000   0.0088
  -9.500  -0.7610   0.04231   0.03798  -0.0410   1.0000   0.0090
  -9.250  -0.7668   0.03809   0.03333  -0.0395   1.0000   0.0091
  -9.000  -0.7636   0.03472   0.02957  -0.0381   1.0000   0.0094
  -8.750  -0.7546   0.03196   0.02644  -0.0368   1.0000   0.0099
  -8.500  -0.7410   0.02987   0.02400  -0.0355   1.0000   0.0108
  -8.250  -0.7254   0.02793   0.02170  -0.0343   1.0000   0.0114
  -8.000  -0.7115   0.02544   0.01889  -0.0328   1.0000   0.0119
  -7.750  -0.6952   0.02360   0.01684  -0.0314   1.0000   0.0126
  -7.500  -0.6771   0.02229   0.01540  -0.0302   1.0000   0.0133
  -7.250  -0.6586   0.02113   0.01406  -0.0288   1.0000   0.0142
  -7.000  -0.6403   0.02000   0.01279  -0.0274   1.0000   0.0152
  -6.750  -0.6218   0.01909   0.01175  -0.0259   1.0000   0.0167
  -6.500  -0.6048   0.01811   0.01070  -0.0243   1.0000   0.0187
  -6.250  -0.5823   0.01740   0.00995  -0.0238   0.9981   0.0213
  -6.000  -0.5494   0.01651   0.00891  -0.0252   0.9912   0.0250
  -5.750  -0.5162   0.01563   0.00801  -0.0269   0.9849   0.0313
  -5.500  -0.4836   0.01500   0.00728  -0.0282   0.9778   0.0394
  -5.250  -0.4489   0.01453   0.00674  -0.0299   0.9719   0.0486
  -5.000  -0.4179   0.01397   0.00617  -0.0310   0.9633   0.0592
  -4.750  -0.3843   0.01345   0.00565  -0.0325   0.9566   0.0729
  -4.500  -0.3537   0.01295   0.00517  -0.0333   0.9473   0.0898
  -4.250  -0.3226   0.01245   0.00470  -0.0343   0.9389   0.1150
  -4.000  -0.2921   0.01189   0.00432  -0.0352   0.9305   0.1599
  -3.500  -0.2364   0.01071   0.00367  -0.0360   0.9122   0.3060
  -3.250  -0.2109   0.01006   0.00343  -0.0359   0.9032   0.4217
  -3.000  -0.1856   0.00970   0.00334  -0.0353   0.8936   0.5045
  -2.750  -0.1590   0.00952   0.00328  -0.0349   0.8851   0.5603
  -2.500  -0.1328   0.00941   0.00325  -0.0343   0.8760   0.6053
  -2.250  -0.1068   0.00935   0.00323  -0.0336   0.8670   0.6412
  -2.000  -0.0802   0.00932   0.00320  -0.0331   0.8590   0.6686
  -1.750  -0.0538   0.00931   0.00316  -0.0325   0.8497   0.6882
  -1.500  -0.0270   0.00929   0.00311  -0.0321   0.8411   0.7028
  -1.250  -0.0002   0.00929   0.00305  -0.0316   0.8326   0.7173
  -1.000   0.0262   0.00928   0.00304  -0.0311   0.8232   0.7331
  -0.750   0.0526   0.00927   0.00303  -0.0306   0.8147   0.7483
  -0.500   0.0789   0.00927   0.00302  -0.0300   0.8059   0.7627
  -0.250   0.1054   0.00926   0.00300  -0.0296   0.7963   0.7753
   0.000   0.1318   0.00924   0.00297  -0.0290   0.7855   0.7848
   0.250   0.1582   0.00923   0.00293  -0.0285   0.7733   0.7944
   0.500   0.1846   0.00922   0.00289  -0.0280   0.7605   0.8046
   0.750   0.2109   0.00920   0.00287  -0.0274   0.7477   0.8147
   1.000   0.2371   0.00919   0.00285  -0.0268   0.7338   0.8249
   1.250   0.2634   0.00918   0.00285  -0.0263   0.7203   0.8358
   1.500   0.2898   0.00918   0.00287  -0.0258   0.7080   0.8475
   1.750   0.3163   0.00918   0.00290  -0.0254   0.6954   0.8598
   2.000   0.3430   0.00919   0.00294  -0.0249   0.6819   0.8730
   2.500   0.3991   0.00923   0.00304  -0.0245   0.6508   0.9031
   2.750   0.4300   0.00927   0.00311  -0.0250   0.6308   0.9200
   3.000   0.4630   0.00935   0.00317  -0.0260   0.6047   0.9397
   3.250   0.4973   0.00948   0.00326  -0.0273   0.5699   0.9609
   3.500   0.5317   0.00968   0.00333  -0.0288   0.5258   0.9846
   3.750   0.5601   0.01003   0.00345  -0.0291   0.4695   1.0000
   4.000   0.5807   0.01050   0.00364  -0.0279   0.4092   1.0000
   4.250   0.6020   0.01100   0.00392  -0.0270   0.3538   1.0000
   4.500   0.6241   0.01150   0.00423  -0.0262   0.3088   1.0000
   4.750   0.6467   0.01199   0.00457  -0.0255   0.2739   1.0000
   5.000   0.6699   0.01245   0.00493  -0.0249   0.2455   1.0000
   5.250   0.6934   0.01289   0.00530  -0.0243   0.2181   1.0000
   5.500   0.7171   0.01333   0.00571  -0.0237   0.1913   1.0000
   5.750   0.7402   0.01383   0.00612  -0.0232   0.1610   1.0000
   6.000   0.7627   0.01442   0.00658  -0.0225   0.1298   1.0000
   6.250   0.7848   0.01506   0.00711  -0.0218   0.1047   1.0000
   6.500   0.8073   0.01568   0.00767  -0.0212   0.0850   1.0000
   6.750   0.8295   0.01631   0.00827  -0.0205   0.0701   1.0000
   7.000   0.8517   0.01695   0.00895  -0.0198   0.0584   1.0000
   7.250   0.8736   0.01762   0.00967  -0.0190   0.0497   1.0000
   7.500   0.8949   0.01836   0.01041  -0.0182   0.0401   1.0000
   7.750   0.9161   0.01908   0.01109  -0.0174   0.0301   1.0000
   8.000   0.9370   0.01983   0.01188  -0.0166   0.0235   1.0000
   8.250   0.9566   0.02074   0.01288  -0.0156   0.0189   1.0000
   8.500   0.9747   0.02181   0.01401  -0.0144   0.0155   1.0000
   8.750   0.9907   0.02310   0.01549  -0.0129   0.0135   1.0000
   9.000   1.0068   0.02433   0.01688  -0.0114   0.0121   1.0000
   9.250   1.0227   0.02553   0.01820  -0.0100   0.0110   1.0000
   9.500   1.0368   0.02682   0.01959  -0.0086   0.0099   1.0000
   9.750   1.0474   0.02849   0.02139  -0.0068   0.0092   1.0000
  10.000   1.0607   0.02982   0.02292  -0.0052   0.0086   1.0000
  10.250   1.0711   0.03130   0.02460  -0.0034   0.0081   1.0000
  10.500   1.0773   0.03300   0.02649  -0.0011   0.0077   1.0000
  10.750   1.0814   0.03486   0.02854   0.0012   0.0075   1.0000
  11.000   1.0842   0.03680   0.03068   0.0033   0.0072   1.0000
  11.250   1.0849   0.03894   0.03302   0.0050   0.0070   1.0000
  11.500   1.0838   0.04127   0.03555   0.0065   0.0068   1.0000
  11.750   1.0800   0.04404   0.03857   0.0076   0.0067   1.0000
  12.000   1.0752   0.04695   0.04167   0.0081   0.0066   1.0000
  12.250   1.0670   0.05058   0.04553   0.0082   0.0066   1.0000
  12.500   1.0572   0.05459   0.04976   0.0075   0.0066   1.0000
  12.750   1.0462   0.05904   0.05438   0.0060   0.0064   1.0000
  13.000   1.0298   0.06487   0.06047   0.0034   0.0065   1.0000
  13.250   1.0130   0.07135   0.06717  -0.0002   0.0066   1.0000
  13.500   0.9946   0.07881   0.07481  -0.0049   0.0065   1.0000
  13.750   0.9667   0.08940   0.08567  -0.0118   0.0068   1.0000
  14.000   0.9376   0.10151   0.09794  -0.0196   0.0069   1.0000
  14.250   0.8952   0.11820   0.11480  -0.0294   0.0073   1.0000
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