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HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/9 AIRFOIL (hq209-il)
Reynolds number: 200,000
Max Cl/Cd: 74.24 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq209-il-200000.txt
Download as CSV file: xf-hq209-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/9 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4505   0.10425   0.10064  -0.0216   1.0000   0.0367
  -9.500  -0.4486   0.10055   0.09697  -0.0235   1.0000   0.0378
  -9.250  -0.4487   0.09660   0.09306  -0.0261   1.0000   0.0393
  -9.000  -0.3774   0.08228   0.07907  -0.0317   1.0000   0.0436
  -8.750  -0.3701   0.07937   0.07617  -0.0310   1.0000   0.0457
  -8.500  -0.3707   0.07544   0.07227  -0.0321   1.0000   0.0469
  -8.250  -0.3742   0.07118   0.06805  -0.0335   1.0000   0.0485
  -7.500  -0.4931   0.06423   0.06076  -0.0490   1.0000   0.0422
  -7.250  -0.4778   0.06321   0.05999  -0.0446   1.0000   0.0453
  -7.000  -0.4793   0.05989   0.05663  -0.0447   1.0000   0.0463
  -6.750  -0.4814   0.05705   0.05374  -0.0440   1.0000   0.0493
  -6.500  -0.4852   0.05390   0.05042  -0.0430   1.0000   0.0517
  -6.250  -0.4876   0.05367   0.04952  -0.0412   1.0000   0.0542
  -6.000  -0.4891   0.04654   0.04254  -0.0407   1.0000   0.0559
  -5.750  -0.4813   0.04394   0.03995  -0.0392   1.0000   0.0574
  -5.500  -0.4717   0.04153   0.03745  -0.0380   1.0000   0.0597
  -5.250  -0.4437   0.03782   0.03300  -0.0407   0.9969   0.0689
  -5.000  -0.4058   0.02688   0.02079  -0.0408   0.9947   0.0308
  -4.750  -0.3707   0.02445   0.01801  -0.0422   0.9910   0.0290
  -4.500  -0.3363   0.02154   0.01463  -0.0436   0.9874   0.0289
  -4.250  -0.2993   0.01958   0.01231  -0.0452   0.9842   0.0299
  -4.000  -0.2644   0.01764   0.01028  -0.0471   0.9813   0.0356
  -3.750  -0.2316   0.01636   0.00888  -0.0478   0.9762   0.0394
  -3.500  -0.1961   0.01498   0.00749  -0.0494   0.9721   0.0487
  -3.250  -0.1573   0.01397   0.00650  -0.0519   0.9690   0.0777
  -3.000  -0.1265   0.01320   0.00591  -0.0529   0.9624   0.1222
  -2.750  -0.0971   0.01109   0.00550  -0.0547   0.9581   0.4976
  -2.500  -0.0618   0.01081   0.00562  -0.0558   0.9542   0.6441
  -2.250  -0.0325   0.01078   0.00560  -0.0558   0.9468   0.6947
  -2.000   0.0053   0.01074   0.00558  -0.0573   0.9430   0.7383
  -1.750   0.0369   0.01073   0.00556  -0.0576   0.9369   0.7699
  -1.500   0.0695   0.01066   0.00550  -0.0580   0.9310   0.7996
  -1.250   0.1031   0.01055   0.00539  -0.0585   0.9265   0.8302
  -1.000   0.1275   0.01044   0.00532  -0.0571   0.9180   0.8569
  -0.750   0.1582   0.01024   0.00515  -0.0568   0.9131   0.8821
  -0.500   0.1833   0.01012   0.00503  -0.0558   0.9041   0.9026
  -0.250   0.2174   0.00997   0.00485  -0.0565   0.8982   0.9190
   0.000   0.2521   0.00981   0.00468  -0.0575   0.8891   0.9372
   0.250   0.2916   0.00965   0.00448  -0.0595   0.8795   0.9553
   0.500   0.3357   0.00945   0.00423  -0.0624   0.8709   0.9712
   0.750   0.3796   0.00929   0.00403  -0.0656   0.8600   0.9889
   1.000   0.4098   0.00922   0.00392  -0.0664   0.8476   1.0000
   1.250   0.4307   0.00925   0.00390  -0.0652   0.8357   1.0000
   1.500   0.4551   0.00928   0.00388  -0.0645   0.8243   1.0000
   1.750   0.4807   0.00930   0.00386  -0.0640   0.8129   1.0000
   2.000   0.5067   0.00932   0.00384  -0.0634   0.8009   1.0000
   2.250   0.5328   0.00933   0.00385  -0.0628   0.7884   1.0000
   2.500   0.5587   0.00936   0.00385  -0.0622   0.7745   1.0000
   2.750   0.5845   0.00939   0.00388  -0.0616   0.7592   1.0000
   3.000   0.6103   0.00942   0.00391  -0.0609   0.7422   1.0000
   3.250   0.6361   0.00946   0.00394  -0.0602   0.7238   1.0000
   3.500   0.6617   0.00952   0.00401  -0.0595   0.7027   1.0000
   3.750   0.6870   0.00960   0.00406  -0.0587   0.6780   1.0000
   4.000   0.7116   0.00972   0.00413  -0.0577   0.6461   1.0000
   4.250   0.7350   0.00990   0.00419  -0.0565   0.6024   1.0000
   4.500   0.7569   0.01023   0.00432  -0.0551   0.5425   1.0000
   4.750   0.7776   0.01075   0.00453  -0.0537   0.4733   1.0000
   5.000   0.7980   0.01138   0.00487  -0.0524   0.4091   1.0000
   5.250   0.8191   0.01202   0.00529  -0.0514   0.3570   1.0000
   5.500   0.8405   0.01266   0.00574  -0.0504   0.3121   1.0000
   5.750   0.8620   0.01332   0.00624  -0.0495   0.2734   1.0000
   6.000   0.8835   0.01398   0.00680  -0.0487   0.2363   1.0000
   6.250   0.9045   0.01470   0.00734  -0.0478   0.1828   1.0000
   6.500   0.9212   0.01601   0.00819  -0.0464   0.1116   1.0000
   6.750   0.9391   0.01723   0.00924  -0.0449   0.0876   1.0000
   7.000   0.9581   0.01830   0.01028  -0.0437   0.0752   1.0000
   7.250   0.9774   0.01930   0.01126  -0.0426   0.0652   1.0000
   7.500   0.9988   0.02005   0.01218  -0.0416   0.0577   1.0000
   7.750   1.0184   0.02098   0.01314  -0.0407   0.0493   1.0000
   8.000   1.0365   0.02204   0.01421  -0.0396   0.0399   1.0000
   8.250   1.0524   0.02355   0.01582  -0.0379   0.0284   1.0000
   8.500   1.0698   0.02495   0.01735  -0.0363   0.0227   1.0000
   8.750   1.0819   0.02819   0.02065  -0.0343   0.0200   1.0000
   9.000   1.1008   0.03004   0.02275  -0.0329   0.0190   1.0000
   9.250   1.1181   0.03252   0.02554  -0.0315   0.0182   1.0000
   9.500   1.1327   0.03530   0.02865  -0.0298   0.0177   1.0000
   9.750   1.1446   0.03736   0.03099  -0.0280   0.0164   1.0000
  10.000   1.1539   0.03950   0.03343  -0.0261   0.0155   1.0000
  10.250   1.1612   0.04101   0.03508  -0.0243   0.0145   1.0000
  10.500   1.1623   0.04351   0.03781  -0.0218   0.0140   1.0000
  10.750   1.1564   0.04650   0.04109  -0.0186   0.0139   1.0000
  11.000   1.1462   0.04972   0.04461  -0.0157   0.0139   1.0000
  11.250   1.1322   0.05335   0.04855  -0.0134   0.0140   1.0000
  11.500   1.1145   0.05759   0.05309  -0.0120   0.0142   1.0000
  11.750   1.0947   0.06239   0.05817  -0.0118   0.0143   1.0000
  12.000   1.0754   0.06749   0.06349  -0.0129   0.0143   1.0000
  12.250   1.0484   0.07461   0.07088  -0.0158   0.0147   1.0000
  12.500   1.0158   0.08386   0.08040  -0.0215   0.0152   1.0000
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