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HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il)
Reynolds number: 500,000
Max Cl/Cd: 67.99 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq159b-il-500000-n5.txt
Download as CSV file: xf-hq159b-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/9 B AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5152   0.09666   0.09433  -0.0167   1.0000   0.0070
  -9.750  -0.5191   0.09114   0.08883  -0.0193   1.0000   0.0066
  -9.500  -0.5350   0.08197   0.07973  -0.0238   1.0000   0.0058
  -9.250  -0.5271   0.08062   0.07837  -0.0249   1.0000   0.0065
  -9.000  -0.5295   0.07608   0.07387  -0.0278   1.0000   0.0070
  -8.750  -0.5734   0.06006   0.05790  -0.0411   1.0000   0.0058
  -8.500  -0.5906   0.05239   0.05009  -0.0444   1.0000   0.0056
  -8.250  -0.6002   0.04537   0.04284  -0.0455   1.0000   0.0055
  -8.000  -0.6019   0.03999   0.03719  -0.0452   1.0000   0.0055
  -7.750  -0.6039   0.03505   0.03190  -0.0442   1.0000   0.0055
  -7.500  -0.5979   0.03084   0.02731  -0.0434   0.9987   0.0056
  -7.250  -0.5751   0.02700   0.02307  -0.0452   0.9905   0.0059
  -7.000  -0.5472   0.02484   0.02066  -0.0470   0.9847   0.0064
  -6.750  -0.5186   0.02288   0.01844  -0.0484   0.9786   0.0068
  -6.500  -0.4894   0.02070   0.01591  -0.0496   0.9720   0.0070
  -6.250  -0.4603   0.01833   0.01314  -0.0503   0.9653   0.0067
  -6.000  -0.4308   0.01659   0.01110  -0.0509   0.9577   0.0065
  -5.750  -0.4023   0.01527   0.00956  -0.0512   0.9490   0.0064
  -5.500  -0.3740   0.01426   0.00838  -0.0513   0.9401   0.0062
  -5.250  -0.3475   0.01338   0.00736  -0.0511   0.9295   0.0062
  -5.000  -0.3216   0.01264   0.00649  -0.0507   0.9184   0.0062
  -4.750  -0.2959   0.01200   0.00574  -0.0503   0.9076   0.0062
  -4.500  -0.2702   0.01141   0.00506  -0.0499   0.8974   0.0062
  -4.250  -0.2444   0.01091   0.00446  -0.0494   0.8872   0.0063
  -4.000  -0.2183   0.01050   0.00395  -0.0490   0.8770   0.0063
  -3.750  -0.1921   0.01012   0.00345  -0.0487   0.8671   0.0066
  -3.500  -0.1655   0.00984   0.00306  -0.0483   0.8578   0.0068
  -3.250  -0.1387   0.00958   0.00270  -0.0480   0.8482   0.0073
  -3.000  -0.1117   0.00937   0.00240  -0.0478   0.8394   0.0080
  -2.750  -0.0845   0.00920   0.00214  -0.0475   0.8310   0.0090
  -2.500  -0.0571   0.00905   0.00194  -0.0474   0.8220   0.0115
  -2.250  -0.0303   0.00876   0.00177  -0.0472   0.8132   0.0438
  -2.000  -0.0035   0.00852   0.00162  -0.0471   0.8039   0.0764
  -1.750   0.0226   0.00808   0.00146  -0.0470   0.7925   0.1663
  -1.500   0.0487   0.00764   0.00130  -0.0469   0.7809   0.2641
  -1.250   0.0712   0.00656   0.00120  -0.0465   0.7702   0.5488
  -1.000   0.0974   0.00641   0.00121  -0.0461   0.7598   0.6156
  -0.750   0.1245   0.00638   0.00120  -0.0458   0.7485   0.6473
  -0.500   0.1518   0.00636   0.00119  -0.0456   0.7368   0.6669
  -0.250   0.1788   0.00635   0.00119  -0.0453   0.7250   0.6931
   0.000   0.2058   0.00635   0.00120  -0.0450   0.7130   0.7136
   0.250   0.2331   0.00637   0.00120  -0.0448   0.6992   0.7253
   0.500   0.2605   0.00640   0.00120  -0.0446   0.6850   0.7352
   0.750   0.2879   0.00644   0.00122  -0.0445   0.6721   0.7456
   1.000   0.3151   0.00646   0.00125  -0.0443   0.6587   0.7566
   1.250   0.3423   0.00650   0.00128  -0.0441   0.6451   0.7679
   1.500   0.3696   0.00654   0.00133  -0.0439   0.6301   0.7779
   1.750   0.3967   0.00660   0.00137  -0.0437   0.6128   0.7877
   2.000   0.4234   0.00667   0.00143  -0.0434   0.5925   0.7982
   2.250   0.4490   0.00683   0.00149  -0.0429   0.5532   0.8095
   2.500   0.4714   0.00732   0.00163  -0.0419   0.4629   0.8223
   2.750   0.4941   0.00781   0.00183  -0.0411   0.3809   0.8380
   3.000   0.5165   0.00828   0.00203  -0.0402   0.3040   0.8595
   3.250   0.5395   0.00855   0.00222  -0.0393   0.2632   0.8890
   3.500   0.5659   0.00872   0.00239  -0.0390   0.2379   0.9324
   3.750   0.6045   0.00897   0.00260  -0.0415   0.2129   0.9995
   4.000   0.6303   0.00927   0.00280  -0.0413   0.1875   1.0000
   4.250   0.6551   0.00971   0.00303  -0.0410   0.1406   1.0000
   4.500   0.6787   0.01030   0.00337  -0.0405   0.0923   1.0000
   4.750   0.7027   0.01085   0.00376  -0.0401   0.0567   1.0000
   5.000   0.7270   0.01135   0.00413  -0.0397   0.0335   1.0000
   5.250   0.7524   0.01172   0.00448  -0.0393   0.0277   1.0000
   5.500   0.7781   0.01203   0.00483  -0.0390   0.0261   1.0000
   5.750   0.8036   0.01235   0.00521  -0.0387   0.0252   1.0000
   6.000   0.8288   0.01271   0.00562  -0.0383   0.0242   1.0000
   6.250   0.8537   0.01311   0.00610  -0.0379   0.0231   1.0000
   6.500   0.8783   0.01353   0.00658  -0.0374   0.0218   1.0000
   6.750   0.9023   0.01402   0.00711  -0.0369   0.0206   1.0000
   7.000   0.9257   0.01459   0.00774  -0.0363   0.0196   1.0000
   7.250   0.9481   0.01528   0.00851  -0.0355   0.0186   1.0000
   7.500   0.9688   0.01617   0.00950  -0.0345   0.0177   1.0000
   7.750   0.9872   0.01740   0.01086  -0.0332   0.0168   1.0000
   8.000   1.0107   0.01786   0.01138  -0.0327   0.0165   1.0000
   8.250   1.0338   0.01834   0.01196  -0.0321   0.0161   1.0000
   8.500   1.0557   0.01899   0.01270  -0.0314   0.0155   1.0000
   8.750   1.0768   0.01974   0.01356  -0.0305   0.0150   1.0000
   9.000   1.0977   0.02048   0.01440  -0.0297   0.0142   1.0000
   9.250   1.1196   0.02099   0.01498  -0.0290   0.0133   1.0000
   9.500   1.1428   0.02121   0.01522  -0.0286   0.0123   1.0000
   9.750   1.1642   0.02166   0.01571  -0.0280   0.0114   1.0000
  10.000   1.1798   0.02285   0.01700  -0.0266   0.0106   1.0000
  10.250   1.2017   0.02319   0.01743  -0.0260   0.0101   1.0000
  10.500   1.2222   0.02366   0.01800  -0.0252   0.0093   1.0000
  10.750   1.2422   0.02413   0.01853  -0.0244   0.0084   1.0000
  11.000   1.2632   0.02442   0.01885  -0.0238   0.0077   1.0000
  11.250   1.2817   0.02495   0.01938  -0.0228   0.0070   1.0000
  11.500   1.2952   0.02586   0.02044  -0.0212   0.0064   1.0000
  11.750   1.3057   0.02682   0.02153  -0.0190   0.0059   1.0000
  12.000   1.3158   0.02776   0.02258  -0.0170   0.0054   1.0000
  12.250   1.3261   0.02869   0.02359  -0.0152   0.0049   1.0000
  12.500   1.3343   0.02982   0.02480  -0.0133   0.0044   1.0000
  12.750   1.3383   0.03134   0.02644  -0.0113   0.0040   1.0000
  13.000   1.3404   0.03309   0.02836  -0.0094   0.0038   1.0000
  13.250   1.3411   0.03505   0.03049  -0.0078   0.0036   1.0000
  13.500   1.3411   0.03721   0.03281  -0.0066   0.0034   1.0000
  13.750   1.3380   0.03980   0.03558  -0.0056   0.0033   1.0000
  14.000   1.3357   0.04249   0.03842  -0.0051   0.0031   1.0000
  14.250   1.3288   0.04587   0.04198  -0.0050   0.0031   1.0000
  14.500   1.3222   0.04948   0.04576  -0.0055   0.0029   1.0000
  14.750   1.3120   0.05386   0.05031  -0.0067   0.0029   1.0000
  15.000   1.3003   0.05884   0.05545  -0.0087   0.0028   1.0000
  15.250   1.2841   0.06502   0.06183  -0.0117   0.0028   1.0000
  15.500   1.2660   0.07222   0.06920  -0.0158   0.0027   1.0000
  15.750   1.2431   0.08099   0.07817  -0.0211   0.0028   1.0000
  16.000   1.2155   0.09148   0.08886  -0.0276   0.0029   1.0000
  16.250   1.1791   0.10456   0.10214  -0.0354   0.0031   1.0000
  16.500   1.1405   0.11847   0.11622  -0.0436   0.0032   1.0000
  16.750   1.0900   0.13617   0.13408  -0.0537   0.0035   1.0000
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