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HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/9 AIRFOIL (hq159-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.89 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq159-il-1000000.txt
Download as CSV file: xf-hq159-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/9 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4354   0.09886   0.09733  -0.0164   1.0000   0.0088
 -10.500  -0.4374   0.09387   0.09235  -0.0182   1.0000   0.0089
 -10.250  -0.4394   0.08902   0.08751  -0.0199   1.0000   0.0090
 -10.000  -0.4422   0.08385   0.08235  -0.0218   1.0000   0.0090
  -9.750  -0.4444   0.07914   0.07766  -0.0235   1.0000   0.0092
  -9.500  -0.4511   0.07322   0.07175  -0.0258   1.0000   0.0092
  -9.250  -0.4588   0.06724   0.06579  -0.0284   1.0000   0.0092
  -9.000  -0.4708   0.06038   0.05894  -0.0317   1.0000   0.0093
  -8.750  -0.5060   0.04616   0.04473  -0.0427   1.0000   0.0089
  -8.500  -0.5310   0.04014   0.03861  -0.0460   1.0000   0.0088
  -8.250  -0.5498   0.03496   0.03328  -0.0463   1.0000   0.0088
  -8.000  -0.5616   0.02965   0.02777  -0.0462   1.0000   0.0088
  -7.750  -0.5674   0.02526   0.02319  -0.0450   1.0000   0.0090
  -7.500  -0.6304   0.02164   0.01804  -0.0406   0.9983   0.0054
  -7.250  -0.6011   0.01844   0.01440  -0.0422   0.9951   0.0053
  -7.000  -0.5723   0.01578   0.01138  -0.0434   0.9916   0.0056
  -6.750  -0.5409   0.01451   0.00997  -0.0447   0.9880   0.0060
  -6.500  -0.5074   0.01384   0.00921  -0.0462   0.9852   0.0066
  -6.250  -0.4734   0.01290   0.00815  -0.0478   0.9828   0.0071
  -6.000  -0.4428   0.01213   0.00727  -0.0486   0.9769   0.0076
  -5.750  -0.4110   0.01132   0.00636  -0.0496   0.9711   0.0079
  -5.500  -0.3812   0.01067   0.00562  -0.0501   0.9630   0.0082
  -5.250  -0.3525   0.01004   0.00489  -0.0504   0.9540   0.0086
  -5.000  -0.3278   0.00914   0.00382  -0.0498   0.9418   0.0101
  -4.750  -0.3019   0.00876   0.00336  -0.0493   0.9301   0.0113
  -4.500  -0.2757   0.00847   0.00300  -0.0489   0.9190   0.0129
  -4.250  -0.2498   0.00807   0.00253  -0.0483   0.9086   0.0184
  -4.000  -0.2236   0.00780   0.00227  -0.0480   0.8989   0.0335
  -3.750  -0.1969   0.00761   0.00209  -0.0477   0.8892   0.0447
  -3.500  -0.1701   0.00743   0.00191  -0.0475   0.8800   0.0576
  -3.250  -0.1435   0.00722   0.00174  -0.0473   0.8709   0.0785
  -3.000  -0.1173   0.00690   0.00156  -0.0470   0.8610   0.1263
  -2.750  -0.0917   0.00640   0.00138  -0.0469   0.8514   0.2229
  -2.500  -0.0661   0.00594   0.00120  -0.0466   0.8428   0.3235
  -2.250  -0.0407   0.00542   0.00108  -0.0464   0.8341   0.4521
  -2.000  -0.0142   0.00518   0.00102  -0.0462   0.8251   0.5241
  -1.750   0.0127   0.00506   0.00096  -0.0460   0.8149   0.5665
  -1.500   0.0399   0.00499   0.00092  -0.0458   0.8038   0.5976
  -1.250   0.0673   0.00493   0.00089  -0.0456   0.7931   0.6266
  -1.000   0.0948   0.00489   0.00088  -0.0454   0.7831   0.6530
  -0.750   0.1222   0.00487   0.00087  -0.0452   0.7732   0.6752
  -0.500   0.1494   0.00485   0.00086  -0.0450   0.7622   0.6991
  -0.250   0.1770   0.00484   0.00086  -0.0449   0.7506   0.7154
   0.000   0.2046   0.00485   0.00086  -0.0447   0.7396   0.7290
   0.250   0.2322   0.00486   0.00087  -0.0446   0.7289   0.7423
   0.500   0.2597   0.00487   0.00088  -0.0444   0.7181   0.7552
   0.750   0.2871   0.00489   0.00090  -0.0443   0.7062   0.7693
   1.000   0.3146   0.00491   0.00093  -0.0441   0.6938   0.7815
   1.250   0.3421   0.00494   0.00095  -0.0440   0.6804   0.7919
   1.500   0.3695   0.00498   0.00099  -0.0438   0.6663   0.8029
   1.750   0.3966   0.00503   0.00102  -0.0436   0.6504   0.8143
   2.000   0.4236   0.00507   0.00106  -0.0434   0.6304   0.8264
   2.250   0.4500   0.00515   0.00111  -0.0430   0.6044   0.8397
   2.500   0.4759   0.00526   0.00118  -0.0426   0.5724   0.8551
   2.750   0.5008   0.00541   0.00126  -0.0420   0.5313   0.8743
   3.000   0.5239   0.00564   0.00137  -0.0410   0.4734   0.9041
   3.250   0.5543   0.00597   0.00153  -0.0417   0.4030   0.9642
   3.500   0.5895   0.00637   0.00171  -0.0437   0.3416   1.0000
   3.750   0.6144   0.00675   0.00189  -0.0433   0.2953   1.0000
   4.000   0.6395   0.00711   0.00209  -0.0429   0.2572   1.0000
   4.250   0.6653   0.00739   0.00227  -0.0426   0.2304   1.0000
   4.500   0.6911   0.00767   0.00246  -0.0424   0.2058   1.0000
   4.750   0.7168   0.00797   0.00265  -0.0421   0.1798   1.0000
   5.000   0.7417   0.00836   0.00289  -0.0417   0.1439   1.0000
   5.250   0.7652   0.00892   0.00322  -0.0412   0.0980   1.0000
   5.500   0.7891   0.00944   0.00356  -0.0407   0.0659   1.0000
   5.750   0.8141   0.00982   0.00388  -0.0403   0.0501   1.0000
   6.000   0.8393   0.01017   0.00418  -0.0400   0.0404   1.0000
   6.250   0.8649   0.01046   0.00447  -0.0397   0.0347   1.0000
   6.500   0.8899   0.01082   0.00480  -0.0393   0.0277   1.0000
   6.750   0.9152   0.01113   0.00510  -0.0390   0.0227   1.0000
   7.000   0.9387   0.01169   0.00556  -0.0384   0.0103   1.0000
   7.250   0.9622   0.01227   0.00614  -0.0377   0.0063   1.0000
   7.500   0.9859   0.01280   0.00673  -0.0370   0.0054   1.0000
   7.750   1.0091   0.01341   0.00742  -0.0363   0.0049   1.0000
   8.000   1.0305   0.01424   0.00838  -0.0353   0.0045   1.0000
   8.250   1.0530   0.01487   0.00909  -0.0345   0.0043   1.0000
   8.500   1.0751   0.01553   0.00984  -0.0337   0.0042   1.0000
   8.750   1.0958   0.01635   0.01076  -0.0327   0.0041   1.0000
   9.000   1.1158   0.01724   0.01176  -0.0315   0.0040   1.0000
   9.250   1.1351   0.01816   0.01280  -0.0304   0.0039   1.0000
   9.500   1.1536   0.01915   0.01393  -0.0291   0.0038   1.0000
   9.750   1.1717   0.02014   0.01503  -0.0279   0.0037   1.0000
  10.000   1.1889   0.02119   0.01620  -0.0265   0.0036   1.0000
  10.250   1.2046   0.02236   0.01750  -0.0250   0.0034   1.0000
  10.500   1.2189   0.02358   0.01886  -0.0234   0.0033   1.0000
  10.750   1.2323   0.02479   0.02019  -0.0217   0.0032   1.0000
  11.000   1.2442   0.02597   0.02147  -0.0199   0.0030   1.0000
  11.250   1.2495   0.02755   0.02322  -0.0171   0.0030   1.0000
  11.500   1.2486   0.02920   0.02501  -0.0136   0.0028   1.0000
  11.750   1.2372   0.03181   0.02784  -0.0096   0.0027   1.0000
  12.000   1.2344   0.03381   0.03001  -0.0070   0.0027   1.0000
  12.250   1.2161   0.03748   0.03393  -0.0043   0.0026   1.0000
  12.500   1.1978   0.04153   0.03822  -0.0027   0.0026   1.0000
  12.750   1.1794   0.04602   0.04293  -0.0024   0.0026   1.0000
  13.000   1.1680   0.05015   0.04723  -0.0030   0.0026   1.0000
  13.250   1.1611   0.05408   0.05128  -0.0043   0.0026   1.0000
  13.500   1.1424   0.06028   0.05767  -0.0072   0.0026   1.0000
  13.750   1.1259   0.06691   0.06446  -0.0110   0.0026   1.0000
  14.000   1.1255   0.07121   0.06884  -0.0137   0.0026   1.0000
  14.250   1.1083   0.07932   0.07710  -0.0189   0.0027   1.0000
  14.500   1.0862   0.08932   0.08725  -0.0253   0.0027   1.0000
  14.750   1.0607   0.10059   0.09865  -0.0322   0.0026   1.0000
  15.000   1.0543   0.10743   0.10557  -0.0361   0.0027   1.0000
  15.250   1.0298   0.11891   0.11718  -0.0426   0.0028   1.0000
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