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HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il)
Reynolds number: 200,000
Max Cl/Cd: 75.1 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3012-il-200000-n5.txt
Download as CSV file: xf-hq3012-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/12 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  -0.3985   0.08905   0.08550  -0.0484   1.0000   0.0141
 -10.000  -0.4076   0.08405   0.08056  -0.0501   1.0000   0.0139
  -9.750  -0.4242   0.07790   0.07452  -0.0524   1.0000   0.0140
  -9.500  -0.4492   0.07083   0.06756  -0.0551   1.0000   0.0143
  -9.250  -0.5221   0.04788   0.04428  -0.0767   0.9832   0.0129
  -9.000  -0.5279   0.03838   0.03406  -0.0845   0.9710   0.0130
  -8.750  -0.5156   0.03411   0.02931  -0.0868   0.9615   0.0135
  -8.500  -0.4954   0.03047   0.02513  -0.0889   0.9554   0.0145
  -8.250  -0.4763   0.02734   0.02146  -0.0895   0.9474   0.0150
  -8.000  -0.4498   0.02479   0.01846  -0.0907   0.9430   0.0154
  -7.750  -0.4280   0.02297   0.01638  -0.0905   0.9351   0.0159
  -7.500  -0.4001   0.02165   0.01491  -0.0913   0.9301   0.0165
  -7.250  -0.3742   0.02066   0.01377  -0.0915   0.9238   0.0173
  -7.000  -0.3474   0.01965   0.01261  -0.0918   0.9178   0.0185
  -6.750  -0.3192   0.01863   0.01142  -0.0921   0.9130   0.0198
  -6.500  -0.2946   0.01783   0.01052  -0.0918   0.9058   0.0217
  -6.250  -0.2660   0.01731   0.00994  -0.0922   0.9008   0.0245
  -6.000  -0.2408   0.01663   0.00911  -0.0918   0.8941   0.0279
  -5.750  -0.2146   0.01600   0.00847  -0.0918   0.8880   0.0323
  -5.500  -0.1879   0.01551   0.00786  -0.0916   0.8822   0.0372
  -5.250  -0.1620   0.01514   0.00747  -0.0915   0.8755   0.0429
  -5.000  -0.1340   0.01480   0.00707  -0.0916   0.8706   0.0503
  -4.750  -0.1083   0.01458   0.00680  -0.0913   0.8635   0.0577
  -4.500  -0.0817   0.01412   0.00628  -0.0912   0.8580   0.0631
  -4.250  -0.0554   0.01375   0.00587  -0.0910   0.8520   0.0688
  -4.000  -0.0291   0.01341   0.00548  -0.0907   0.8457   0.0765
  -3.750  -0.0014   0.01309   0.00509  -0.0907   0.8410   0.0869
  -3.500   0.0242   0.01277   0.00480  -0.0904   0.8339   0.1022
  -3.250   0.0510   0.01239   0.00450  -0.0904   0.8285   0.1323
  -3.000   0.0767   0.01191   0.00426  -0.0903   0.8225   0.2005
  -2.750   0.1014   0.01126   0.00401  -0.0902   0.8162   0.3140
  -2.500   0.1256   0.01065   0.00399  -0.0897   0.8111   0.4858
  -2.250   0.1511   0.01055   0.00403  -0.0892   0.8041   0.5462
  -2.000   0.1784   0.01051   0.00399  -0.0888   0.7986   0.5816
  -1.750   0.2049   0.01051   0.00400  -0.0884   0.7918   0.6103
  -1.500   0.2316   0.01052   0.00402  -0.0878   0.7852   0.6410
  -1.250   0.2578   0.01056   0.00407  -0.0872   0.7783   0.6681
  -1.000   0.2847   0.01057   0.00405  -0.0868   0.7713   0.6835
  -0.750   0.3120   0.01058   0.00403  -0.0865   0.7649   0.6966
  -0.500   0.3390   0.01061   0.00401  -0.0862   0.7579   0.7088
  -0.250   0.3666   0.01060   0.00397  -0.0859   0.7521   0.7166
   0.000   0.3939   0.01062   0.00396  -0.0858   0.7447   0.7240
   0.250   0.4216   0.01061   0.00391  -0.0856   0.7380   0.7304
   0.500   0.4484   0.01062   0.00389  -0.0853   0.7278   0.7385
   0.750   0.4749   0.01061   0.00386  -0.0849   0.7171   0.7451
   1.000   0.5023   0.01062   0.00382  -0.0846   0.7078   0.7534
   1.250   0.5288   0.01063   0.00385  -0.0843   0.6987   0.7607
   1.500   0.5557   0.01066   0.00387  -0.0840   0.6900   0.7691
   1.750   0.5824   0.01068   0.00388  -0.0836   0.6809   0.7774
   2.000   0.6086   0.01070   0.00393  -0.0832   0.6703   0.7862
   2.250   0.6350   0.01074   0.00397  -0.0828   0.6590   0.7959
   2.500   0.6606   0.01076   0.00401  -0.0823   0.6459   0.8056
   2.750   0.6859   0.01080   0.00405  -0.0816   0.6312   0.8165
   3.000   0.7110   0.01085   0.00411  -0.0810   0.6163   0.8285
   3.250   0.7359   0.01089   0.00417  -0.0803   0.6009   0.8424
   3.500   0.7606   0.01094   0.00426  -0.0796   0.5840   0.8588
   3.750   0.7851   0.01100   0.00432  -0.0787   0.5649   0.8810
   4.000   0.8134   0.01107   0.00442  -0.0788   0.5420   0.9186
   4.250   0.8447   0.01126   0.00455  -0.0796   0.5152   1.0000
   4.500   0.8681   0.01156   0.00472  -0.0789   0.4873   1.0000
   4.750   0.8907   0.01192   0.00494  -0.0781   0.4591   1.0000
   5.000   0.9125   0.01232   0.00520  -0.0772   0.4307   1.0000
   5.500   0.9553   0.01318   0.00585  -0.0752   0.3771   1.0000
   5.750   0.9764   0.01363   0.00621  -0.0742   0.3522   1.0000
   6.000   0.9968   0.01412   0.00659  -0.0731   0.3280   1.0000
   6.250   1.0171   0.01461   0.00701  -0.0720   0.3060   1.0000
   6.750   1.0567   0.01562   0.00790  -0.0697   0.2692   1.0000
   7.000   1.0764   0.01613   0.00837  -0.0685   0.2523   1.0000
   7.250   1.0956   0.01665   0.00887  -0.0673   0.2357   1.0000
   7.500   1.1141   0.01719   0.00938  -0.0660   0.2195   1.0000
   7.750   1.1320   0.01775   0.00990  -0.0646   0.2040   1.0000
   8.000   1.1490   0.01832   0.01044  -0.0631   0.1896   1.0000
   8.250   1.1648   0.01888   0.01100  -0.0613   0.1767   1.0000
   8.500   1.1801   0.01948   0.01159  -0.0596   0.1648   1.0000
   8.750   1.1948   0.02013   0.01225  -0.0578   0.1526   1.0000
   9.000   1.2088   0.02083   0.01292  -0.0560   0.1387   1.0000
   9.250   1.2225   0.02157   0.01364  -0.0542   0.1252   1.0000
   9.500   1.2359   0.02235   0.01440  -0.0525   0.1129   1.0000
   9.750   1.2487   0.02318   0.01523  -0.0507   0.1019   1.0000
  10.000   1.2605   0.02410   0.01612  -0.0490   0.0900   1.0000
  10.250   1.2716   0.02511   0.01712  -0.0473   0.0777   1.0000
  10.500   1.2823   0.02617   0.01817  -0.0456   0.0675   1.0000
  10.750   1.2927   0.02726   0.01928  -0.0440   0.0587   1.0000
  11.000   1.3028   0.02842   0.02047  -0.0424   0.0530   1.0000
  11.250   1.3133   0.02957   0.02169  -0.0410   0.0482   1.0000
  11.500   1.3217   0.03091   0.02307  -0.0395   0.0438   1.0000
  11.750   1.3315   0.03216   0.02443  -0.0381   0.0400   1.0000
  12.000   1.3382   0.03372   0.02601  -0.0368   0.0352   1.0000
  12.250   1.3462   0.03521   0.02762  -0.0355   0.0311   1.0000
  12.500   1.3515   0.03697   0.02943  -0.0343   0.0269   1.0000
  12.750   1.3568   0.03879   0.03133  -0.0332   0.0220   1.0000
  13.000   1.3604   0.04082   0.03343  -0.0322   0.0189   1.0000
  13.250   1.3624   0.04306   0.03574  -0.0313   0.0152   1.0000
  13.500   1.3632   0.04553   0.03830  -0.0305   0.0123   1.0000
  13.750   1.3620   0.04827   0.04112  -0.0299   0.0102   1.0000
  14.000   1.3614   0.05106   0.04404  -0.0295   0.0090   1.0000
  14.250   1.3593   0.05413   0.04724  -0.0293   0.0083   1.0000
  14.500   1.3562   0.05745   0.05070  -0.0294   0.0078   1.0000
  14.750   1.3512   0.06116   0.05455  -0.0297   0.0074   1.0000
  15.000   1.3460   0.06508   0.05862  -0.0304   0.0072   1.0000
  15.250   1.3393   0.06942   0.06313  -0.0314   0.0069   1.0000
  15.500   1.3322   0.07398   0.06786  -0.0327   0.0068   1.0000
  15.750   1.3235   0.07902   0.07311  -0.0344   0.0066   1.0000
  16.000   1.3134   0.08452   0.07878  -0.0366   0.0065   1.0000
  16.250   1.3021   0.09043   0.08487  -0.0391   0.0064   1.0000
  16.500   1.2900   0.09672   0.09134  -0.0420   0.0064   1.0000
  16.750   1.2766   0.10349   0.09829  -0.0453   0.0064   1.0000
  17.000   1.2616   0.11078   0.10575  -0.0490   0.0063   1.0000
  17.250   1.2470   0.11817   0.11332  -0.0529   0.0063   1.0000
  17.500   1.2315   0.12595   0.12126  -0.0571   0.0063   1.0000
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