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HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il)
Reynolds number: 500,000
Max Cl/Cd: 90.57 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3512-il-500000-n5.txt
Download as CSV file: xf-hq3512-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/12 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5153   0.03938   0.03679  -0.0988   0.9661   0.0070
 -10.000  -0.5244   0.03097   0.02771  -0.1066   0.9474   0.0070
  -9.750  -0.5158   0.02738   0.02367  -0.1078   0.9350   0.0071
  -9.500  -0.5011   0.02500   0.02095  -0.1081   0.9252   0.0072
  -9.250  -0.4842   0.02304   0.01868  -0.1080   0.9165   0.0074
  -9.000  -0.4657   0.02146   0.01682  -0.1076   0.9083   0.0075
  -8.750  -0.4453   0.02005   0.01515  -0.1072   0.9012   0.0077
  -8.500  -0.4239   0.01894   0.01383  -0.1068   0.8939   0.0078
  -8.250  -0.4014   0.01788   0.01256  -0.1064   0.8874   0.0079
  -8.000  -0.3777   0.01710   0.01162  -0.1061   0.8809   0.0081
  -7.750  -0.3535   0.01639   0.01073  -0.1058   0.8745   0.0083
  -7.500  -0.3309   0.01529   0.00948  -0.1054   0.8686   0.0087
  -7.250  -0.3066   0.01456   0.00864  -0.1051   0.8622   0.0089
  -7.000  -0.2815   0.01394   0.00790  -0.1048   0.8568   0.0091
  -6.750  -0.2561   0.01338   0.00727  -0.1045   0.8507   0.0094
  -6.500  -0.2304   0.01289   0.00667  -0.1043   0.8449   0.0097
  -6.250  -0.2043   0.01244   0.00612  -0.1041   0.8394   0.0101
  -6.000  -0.1780   0.01203   0.00563  -0.1039   0.8334   0.0105
  -5.750  -0.1514   0.01167   0.00517  -0.1038   0.8281   0.0110
  -5.500  -0.1247   0.01134   0.00477  -0.1036   0.8221   0.0115
  -5.250  -0.0980   0.01098   0.00435  -0.1035   0.8163   0.0127
  -5.000  -0.0710   0.01069   0.00401  -0.1034   0.8110   0.0144
  -4.750  -0.0439   0.01040   0.00373  -0.1033   0.8050   0.0189
  -4.500  -0.0166   0.01020   0.00352  -0.1033   0.7995   0.0270
  -4.250   0.0108   0.01000   0.00333  -0.1032   0.7938   0.0331
  -4.000   0.0384   0.00987   0.00314  -0.1032   0.7880   0.0369
  -3.750   0.0659   0.00969   0.00296  -0.1032   0.7825   0.0427
  -3.500   0.0937   0.00956   0.00279  -0.1032   0.7765   0.0471
  -3.250   0.1213   0.00942   0.00261  -0.1031   0.7709   0.0522
  -3.000   0.1491   0.00928   0.00246  -0.1032   0.7649   0.0597
  -2.750   0.1766   0.00913   0.00232  -0.1031   0.7586   0.0729
  -2.500   0.2040   0.00895   0.00219  -0.1031   0.7518   0.0965
  -2.250   0.2311   0.00872   0.00204  -0.1031   0.7431   0.1356
  -2.000   0.2579   0.00842   0.00192  -0.1031   0.7335   0.2051
  -1.750   0.2844   0.00806   0.00178  -0.1031   0.7242   0.2935
  -1.500   0.3106   0.00763   0.00169  -0.1031   0.7153   0.4203
  -1.250   0.3375   0.00744   0.00167  -0.1030   0.7069   0.4908
  -1.000   0.3645   0.00736   0.00168  -0.1028   0.6987   0.5413
  -0.750   0.3917   0.00731   0.00173  -0.1026   0.6911   0.5895
  -0.500   0.4185   0.00731   0.00179  -0.1023   0.6827   0.6296
  -0.250   0.4459   0.00734   0.00182  -0.1021   0.6735   0.6520
   0.000   0.4733   0.00738   0.00184  -0.1020   0.6650   0.6634
   0.250   0.5006   0.00743   0.00185  -0.1018   0.6554   0.6715
   0.500   0.5281   0.00748   0.00187  -0.1017   0.6450   0.6780
   0.750   0.5553   0.00754   0.00189  -0.1015   0.6336   0.6839
   1.000   0.5824   0.00761   0.00192  -0.1013   0.6225   0.6904
   1.250   0.6095   0.00768   0.00196  -0.1012   0.6114   0.6967
   1.500   0.6365   0.00775   0.00201  -0.1010   0.5996   0.7029
   1.750   0.6631   0.00785   0.00207  -0.1008   0.5851   0.7097
   2.000   0.6891   0.00797   0.00214  -0.1004   0.5681   0.7160
   2.250   0.7149   0.00811   0.00222  -0.1000   0.5496   0.7232
   2.500   0.7404   0.00826   0.00232  -0.0995   0.5296   0.7301
   2.750   0.7650   0.00847   0.00244  -0.0990   0.5058   0.7376
   3.000   0.7889   0.00871   0.00259  -0.0983   0.4783   0.7449
   3.250   0.8125   0.00899   0.00276  -0.0975   0.4501   0.7530
   3.500   0.8359   0.00927   0.00296  -0.0968   0.4234   0.7608
   4.000   0.8818   0.00990   0.00339  -0.0952   0.3676   0.7783
   4.250   0.9043   0.01023   0.00363  -0.0943   0.3395   0.7877
   4.500   0.9264   0.01059   0.00389  -0.0934   0.3119   0.7984
   4.750   0.9487   0.01088   0.00414  -0.0925   0.2930   0.8101
   5.000   0.9712   0.01115   0.00439  -0.0916   0.2787   0.8240
   5.250   0.9939   0.01136   0.00464  -0.0907   0.2684   0.8419
   5.500   1.0150   0.01153   0.00488  -0.0895   0.2598   0.8697
   5.750   1.0446   0.01164   0.00512  -0.0901   0.2509   1.0000
   6.000   1.0683   0.01192   0.00539  -0.0895   0.2438   1.0000
   6.250   1.0915   0.01222   0.00567  -0.0889   0.2349   1.0000
   6.500   1.1148   0.01250   0.00595  -0.0882   0.2266   1.0000
   6.750   1.1369   0.01284   0.00625  -0.0874   0.2172   1.0000
   7.000   1.1596   0.01313   0.00653  -0.0866   0.2076   1.0000
   7.250   1.1816   0.01344   0.00685  -0.0858   0.1983   1.0000
   7.500   1.2024   0.01381   0.00718  -0.0848   0.1863   1.0000
   7.750   1.2223   0.01421   0.00753  -0.0836   0.1722   1.0000
   8.000   1.2402   0.01463   0.00790  -0.0821   0.1573   1.0000
   8.250   1.2566   0.01512   0.00833  -0.0803   0.1421   1.0000
   8.500   1.2698   0.01578   0.00888  -0.0781   0.1220   1.0000
   8.750   1.2838   0.01642   0.00944  -0.0760   0.1054   1.0000
   9.000   1.2949   0.01724   0.01014  -0.0737   0.0850   1.0000
   9.250   1.3070   0.01804   0.01084  -0.0715   0.0693   1.0000
   9.500   1.3192   0.01883   0.01158  -0.0695   0.0566   1.0000
   9.750   1.3299   0.01975   0.01242  -0.0673   0.0425   1.0000
  10.000   1.3381   0.02085   0.01343  -0.0649   0.0278   1.0000
  10.250   1.3449   0.02208   0.01461  -0.0625   0.0154   1.0000
  10.500   1.3545   0.02315   0.01568  -0.0605   0.0094   1.0000
  10.750   1.3645   0.02422   0.01678  -0.0586   0.0062   1.0000
  11.000   1.3747   0.02530   0.01790  -0.0569   0.0051   1.0000
  11.250   1.3857   0.02635   0.01902  -0.0553   0.0047   1.0000
  11.500   1.3949   0.02756   0.02030  -0.0537   0.0043   1.0000
  11.750   1.4045   0.02878   0.02160  -0.0521   0.0040   1.0000
  12.000   1.4130   0.03010   0.02302  -0.0506   0.0038   1.0000
  12.250   1.4217   0.03146   0.02449  -0.0492   0.0038   1.0000
  12.500   1.4288   0.03298   0.02612  -0.0479   0.0036   1.0000
  12.750   1.4351   0.03461   0.02785  -0.0466   0.0035   1.0000
  13.000   1.4406   0.03637   0.02972  -0.0454   0.0035   1.0000
  13.250   1.4441   0.03837   0.03183  -0.0442   0.0033   1.0000
  13.500   1.4477   0.04042   0.03399  -0.0432   0.0033   1.0000
  13.750   1.4492   0.04277   0.03645  -0.0423   0.0032   1.0000
  14.000   1.4504   0.04523   0.03902  -0.0416   0.0031   1.0000
  14.250   1.4494   0.04803   0.04194  -0.0411   0.0030   1.0000
  14.500   1.4460   0.05124   0.04527  -0.0407   0.0029   1.0000
  14.750   1.4421   0.05466   0.04882  -0.0407   0.0028   1.0000
  15.000   1.4355   0.05858   0.05288  -0.0409   0.0027   1.0000
  15.250   1.4293   0.06266   0.05709  -0.0415   0.0027   1.0000
  15.500   1.4216   0.06715   0.06173  -0.0424   0.0027   1.0000
  15.750   1.4106   0.07234   0.06707  -0.0438   0.0026   1.0000
  16.000   1.3972   0.07819   0.07307  -0.0457   0.0026   1.0000
  16.250   1.3848   0.08413   0.07916  -0.0478   0.0026   1.0000
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