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HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/8 AIRFOIL (hq158-il)
Reynolds number: 1,000,000
Max Cl/Cd: 91.97 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq158-il-1000000.txt
Download as CSV file: xf-hq158-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4277   0.08266   0.08117  -0.0178   1.0000   0.0080
  -9.000  -0.4295   0.07786   0.07638  -0.0195   1.0000   0.0081
  -8.750  -0.4326   0.07293   0.07146  -0.0214   1.0000   0.0082
  -8.500  -0.4369   0.06793   0.06648  -0.0234   1.0000   0.0083
  -8.250  -0.4437   0.06270   0.06127  -0.0258   1.0000   0.0083
  -8.000  -0.4532   0.05734   0.05593  -0.0287   1.0000   0.0083
  -7.750  -0.4755   0.05125   0.04987  -0.0347   1.0000   0.0079
  -7.500  -0.4863   0.04488   0.04341  -0.0391   1.0000   0.0078
  -7.250  -0.4904   0.03918   0.03761  -0.0412   1.0000   0.0079
  -7.000  -0.4905   0.03414   0.03245  -0.0418   1.0000   0.0081
  -6.750  -0.4883   0.02940   0.02755  -0.0416   0.9996   0.0082
  -6.500  -0.4671   0.02335   0.02122  -0.0450   0.9951   0.0087
  -6.250  -0.4431   0.01871   0.01631  -0.0468   0.9906   0.0096
  -6.000  -0.4110   0.01744   0.01488  -0.0478   0.9863   0.0106
  -5.750  -0.4235   0.01790   0.01391  -0.0468   0.9852   0.0063
  -5.500  -0.3918   0.01473   0.01037  -0.0480   0.9822   0.0057
  -5.250  -0.3628   0.01296   0.00834  -0.0483   0.9755   0.0058
  -5.000  -0.3330   0.01079   0.00588  -0.0488   0.9696   0.0065
  -4.750  -0.3051   0.00989   0.00489  -0.0490   0.9606   0.0076
  -4.500  -0.2770   0.00936   0.00427  -0.0490   0.9511   0.0083
  -4.250  -0.2504   0.00887   0.00368  -0.0487   0.9400   0.0089
  -4.000  -0.2243   0.00857   0.00331  -0.0482   0.9284   0.0099
  -3.750  -0.1983   0.00822   0.00286  -0.0477   0.9168   0.0106
  -3.500  -0.1727   0.00763   0.00211  -0.0470   0.9053   0.0147
  -3.250  -0.1466   0.00729   0.00180  -0.0466   0.8943   0.0352
  -3.000  -0.1202   0.00710   0.00161  -0.0462   0.8828   0.0544
  -2.750  -0.0941   0.00684   0.00144  -0.0459   0.8704   0.0900
  -2.500  -0.0684   0.00649   0.00127  -0.0456   0.8581   0.1581
  -2.250  -0.0439   0.00579   0.00108  -0.0453   0.8471   0.3178
  -2.000  -0.0192   0.00516   0.00096  -0.0450   0.8375   0.4844
  -1.750   0.0072   0.00495   0.00089  -0.0448   0.8278   0.5526
  -1.500   0.0339   0.00485   0.00084  -0.0445   0.8162   0.5963
  -1.250   0.0609   0.00480   0.00081  -0.0442   0.8042   0.6267
  -1.000   0.0880   0.00474   0.00079  -0.0440   0.7933   0.6575
  -0.750   0.1152   0.00469   0.00077  -0.0438   0.7833   0.6856
  -0.500   0.1423   0.00466   0.00077  -0.0435   0.7724   0.7110
  -0.250   0.1692   0.00465   0.00077  -0.0432   0.7603   0.7364
   0.000   0.1963   0.00464   0.00077  -0.0430   0.7481   0.7540
   0.500   0.2506   0.00465   0.00079  -0.0425   0.7244   0.7882
   1.000   0.3046   0.00468   0.00083  -0.0420   0.6970   0.8185
   1.250   0.3315   0.00471   0.00085  -0.0417   0.6809   0.8321
   1.500   0.3582   0.00473   0.00088  -0.0414   0.6626   0.8469
   2.000   0.4096   0.00480   0.00094  -0.0404   0.6125   0.8890
   2.250   0.4384   0.00485   0.00100  -0.0405   0.5691   0.9443
   2.500   0.4801   0.00522   0.00112  -0.0439   0.4908   1.0000
   2.750   0.5043   0.00564   0.00126  -0.0433   0.4226   1.0000
   3.000   0.5287   0.00608   0.00142  -0.0428   0.3551   1.0000
   3.250   0.5540   0.00641   0.00157  -0.0425   0.3133   1.0000
   3.500   0.5802   0.00664   0.00174  -0.0422   0.2981   1.0000
   3.750   0.6064   0.00686   0.00189  -0.0420   0.2611   1.0000
   4.000   0.6318   0.00719   0.00206  -0.0417   0.2262   1.0000
   4.250   0.6575   0.00750   0.00226  -0.0414   0.1970   1.0000
   4.500   0.6821   0.00793   0.00249  -0.0410   0.1489   1.0000
   4.750   0.7057   0.00852   0.00281  -0.0405   0.0942   1.0000
   5.000   0.7301   0.00902   0.00315  -0.0400   0.0598   1.0000
   5.250   0.7553   0.00939   0.00345  -0.0397   0.0432   1.0000
   5.500   0.7807   0.00973   0.00374  -0.0393   0.0322   1.0000
   5.750   0.8058   0.01013   0.00407  -0.0389   0.0187   1.0000
   6.000   0.8295   0.01078   0.00466  -0.0382   0.0069   1.0000
   6.250   0.8541   0.01130   0.00527  -0.0376   0.0059   1.0000
   6.500   0.8790   0.01173   0.00575  -0.0371   0.0053   1.0000
   6.750   0.9033   0.01224   0.00636  -0.0366   0.0049   1.0000
   7.000   0.9270   0.01285   0.00706  -0.0359   0.0047   1.0000
   7.250   0.9505   0.01347   0.00775  -0.0352   0.0044   1.0000
   7.500   0.9731   0.01421   0.00859  -0.0344   0.0041   1.0000
   7.750   0.9932   0.01533   0.00984  -0.0332   0.0036   1.0000
   8.000   1.0067   0.01772   0.01253  -0.0309   0.0032   1.0000
   8.250   1.0280   0.01870   0.01364  -0.0300   0.0031   1.0000
   8.500   1.0462   0.02030   0.01544  -0.0285   0.0030   1.0000
   8.750   1.0624   0.02232   0.01769  -0.0269   0.0029   1.0000
   9.000   1.0748   0.02502   0.02072  -0.0248   0.0029   1.0000
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