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HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il)
Reynolds number: 200,000
Max Cl/Cd: 72.29 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2012-il-200000.txt
Download as CSV file: xf-hq2012-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/12 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4498   0.09039   0.08687  -0.0399   1.0000   0.0605
  -9.750  -0.4144   0.06706   0.06386  -0.0500   1.0000   0.0474
  -9.500  -0.5987   0.05667   0.05285  -0.0614   1.0000   0.0341
  -9.250  -0.6131   0.05311   0.04925  -0.0597   1.0000   0.0334
  -9.000  -0.6298   0.04992   0.04597  -0.0569   1.0000   0.0328
  -8.750  -0.6486   0.04724   0.04317  -0.0528   1.0000   0.0322
  -8.500  -0.6674   0.04464   0.04040  -0.0481   1.0000   0.0317
  -8.250  -0.6822   0.04150   0.03699  -0.0439   1.0000   0.0311
  -8.000  -0.6829   0.03699   0.03200  -0.0424   0.9983   0.0305
  -7.750  -0.6573   0.03213   0.02646  -0.0448   0.9935   0.0307
  -7.500  -0.6279   0.02955   0.02342  -0.0465   0.9882   0.0328
  -7.250  -0.5933   0.02771   0.02104  -0.0485   0.9839   0.0345
  -7.000  -0.5650   0.02417   0.01725  -0.0498   0.9798   0.0366
  -6.750  -0.5324   0.02286   0.01583  -0.0512   0.9747   0.0397
  -6.500  -0.4945   0.02210   0.01478  -0.0534   0.9709   0.0442
  -6.250  -0.4623   0.02027   0.01297  -0.0549   0.9669   0.0504
  -6.000  -0.4311   0.01912   0.01169  -0.0558   0.9612   0.0574
  -5.750  -0.3938   0.01840   0.01093  -0.0580   0.9575   0.0666
  -5.500  -0.3550   0.01739   0.00995  -0.0607   0.9550   0.0770
  -5.250  -0.3281   0.01666   0.00922  -0.0608   0.9476   0.0864
  -5.000  -0.2913   0.01589   0.00847  -0.0629   0.9438   0.0994
  -4.750  -0.2534   0.01508   0.00773  -0.0652   0.9409   0.1175
  -4.500  -0.2280   0.01441   0.00720  -0.0651   0.9331   0.1456
  -4.250  -0.1966   0.01343   0.00660  -0.0664   0.9283   0.2204
  -4.000  -0.1715   0.01236   0.00618  -0.0666   0.9223   0.3574
  -3.750  -0.1475   0.01179   0.00618  -0.0660   0.9154   0.5083
  -3.500  -0.1152   0.01167   0.00617  -0.0664   0.9114   0.5748
  -3.250  -0.0909   0.01175   0.00625  -0.0654   0.9032   0.6123
  -3.000  -0.0605   0.01179   0.00626  -0.0654   0.8981   0.6423
  -2.750  -0.0343   0.01187   0.00634  -0.0646   0.8913   0.6631
  -2.500  -0.0068   0.01194   0.00637  -0.0640   0.8849   0.6829
  -2.250   0.0211   0.01201   0.00639  -0.0635   0.8793   0.7022
  -2.000   0.0459   0.01210   0.00646  -0.0625   0.8714   0.7180
  -1.750   0.0745   0.01211   0.00643  -0.0621   0.8665   0.7327
  -1.500   0.0981   0.01219   0.00651  -0.0609   0.8578   0.7450
  -1.250   0.1258   0.01216   0.00645  -0.0603   0.8523   0.7570
  -1.000   0.1496   0.01222   0.00652  -0.0592   0.8440   0.7695
  -0.750   0.1761   0.01220   0.00648  -0.0583   0.8381   0.7830
  -0.500   0.1996   0.01222   0.00650  -0.0571   0.8296   0.7962
  -0.250   0.2270   0.01211   0.00633  -0.0565   0.8226   0.8074
   0.000   0.2513   0.01202   0.00626  -0.0555   0.8126   0.8152
   0.250   0.2785   0.01188   0.00607  -0.0550   0.8049   0.8241
   0.500   0.3040   0.01178   0.00596  -0.0542   0.7957   0.8331
   0.750   0.3296   0.01166   0.00585  -0.0535   0.7868   0.8420
   1.000   0.3566   0.01151   0.00566  -0.0529   0.7784   0.8521
   1.250   0.3811   0.01139   0.00558  -0.0519   0.7681   0.8621
   1.500   0.4073   0.01127   0.00545  -0.0513   0.7602   0.8725
   1.750   0.4326   0.01116   0.00537  -0.0505   0.7508   0.8842
   2.000   0.4580   0.01107   0.00532  -0.0497   0.7413   0.8970
   2.250   0.4857   0.01095   0.00519  -0.0492   0.7332   0.9105
   2.500   0.5138   0.01088   0.00518  -0.0491   0.7219   0.9253
   2.750   0.5472   0.01081   0.00515  -0.0500   0.7105   0.9409
   3.000   0.5856   0.01075   0.00511  -0.0520   0.6988   0.9565
   3.250   0.6272   0.01070   0.00506  -0.0548   0.6855   0.9720
   3.500   0.6700   0.01065   0.00504  -0.0579   0.6697   0.9890
   3.750   0.6995   0.01065   0.00503  -0.0587   0.6533   1.0000
   4.000   0.7202   0.01070   0.00504  -0.0575   0.6360   1.0000
   4.250   0.7441   0.01078   0.00506  -0.0568   0.6165   1.0000
   4.500   0.7678   0.01087   0.00512  -0.0560   0.5920   1.0000
   4.750   0.7911   0.01102   0.00517  -0.0550   0.5627   1.0000
   5.000   0.8133   0.01125   0.00525  -0.0539   0.5267   1.0000
   5.250   0.8338   0.01161   0.00543  -0.0525   0.4818   1.0000
   5.500   0.8529   0.01212   0.00569  -0.0510   0.4328   1.0000
   5.750   0.8716   0.01272   0.00604  -0.0495   0.3896   1.0000
   6.000   0.8911   0.01330   0.00644  -0.0482   0.3552   1.0000
   6.250   0.9113   0.01386   0.00687  -0.0471   0.3281   1.0000
   6.750   0.9525   0.01495   0.00778  -0.0450   0.2874   1.0000
   7.000   0.9734   0.01548   0.00827  -0.0440   0.2707   1.0000
   7.250   0.9940   0.01601   0.00879  -0.0430   0.2543   1.0000
   7.500   1.0141   0.01653   0.00930  -0.0419   0.2370   1.0000
   7.750   1.0330   0.01709   0.00980  -0.0407   0.2183   1.0000
   8.000   1.0525   0.01755   0.01030  -0.0395   0.1949   1.0000
   8.250   1.0691   0.01819   0.01086  -0.0380   0.1662   1.0000
   8.500   1.0819   0.01912   0.01161  -0.0359   0.1362   1.0000
   8.750   1.0932   0.02018   0.01253  -0.0337   0.1144   1.0000
   9.000   1.1029   0.02123   0.01351  -0.0312   0.1015   1.0000
   9.250   1.1108   0.02239   0.01460  -0.0284   0.0928   1.0000
   9.500   1.1233   0.02331   0.01557  -0.0264   0.0858   1.0000
   9.750   1.1320   0.02464   0.01684  -0.0241   0.0804   1.0000
  10.000   1.1460   0.02557   0.01791  -0.0224   0.0758   1.0000
  10.250   1.1582   0.02668   0.01905  -0.0207   0.0720   1.0000
  10.500   1.1717   0.02831   0.02062  -0.0193   0.0683   1.0000
  10.750   1.1846   0.02923   0.02172  -0.0177   0.0650   1.0000
  11.000   1.1962   0.03027   0.02283  -0.0162   0.0614   1.0000
  11.250   1.2082   0.03200   0.02447  -0.0150   0.0570   1.0000
  11.500   1.2181   0.03300   0.02568  -0.0135   0.0548   1.0000
  11.750   1.2280   0.03420   0.02703  -0.0121   0.0521   1.0000
  12.000   1.2362   0.03548   0.02839  -0.0107   0.0494   1.0000
  12.250   1.2462   0.03754   0.03041  -0.0097   0.0460   1.0000
  12.500   1.2513   0.03886   0.03197  -0.0083   0.0443   1.0000
  12.750   1.2550   0.04038   0.03366  -0.0072   0.0416   1.0000
  13.000   1.2579   0.04200   0.03535  -0.0063   0.0390   1.0000
  13.250   1.2601   0.04450   0.03785  -0.0054   0.0361   1.0000
  13.500   1.2600   0.04665   0.04027  -0.0047   0.0339   1.0000
  13.750   1.2591   0.04903   0.04280  -0.0043   0.0312   1.0000
  14.000   1.2563   0.05184   0.04560  -0.0042   0.0288   1.0000
  14.250   1.2493   0.05550   0.04951  -0.0040   0.0262   1.0000
  14.500   1.2446   0.05893   0.05310  -0.0044   0.0242   1.0000
  14.750   1.2408   0.06227   0.05653  -0.0050   0.0228   1.0000
  15.000   1.2344   0.06628   0.06058  -0.0056   0.0216   1.0000
  15.250   1.2268   0.07075   0.06525  -0.0065   0.0211   1.0000
  15.500   1.2173   0.07563   0.07038  -0.0081   0.0205   1.0000
  15.750   1.2069   0.08090   0.07587  -0.0100   0.0201   1.0000
  16.000   1.1950   0.08664   0.08182  -0.0125   0.0197   1.0000
  16.250   1.1810   0.09301   0.08841  -0.0155   0.0194   1.0000
  16.500   1.1654   0.10001   0.09562  -0.0192   0.0192   1.0000
  16.750   1.1483   0.10760   0.10341  -0.0235   0.0191   1.0000
  17.000   1.1277   0.11631   0.11234  -0.0287   0.0192   1.0000
  17.250   1.1040   0.12623   0.12247  -0.0349   0.0194   1.0000
  17.500   1.0751   0.13798   0.13441  -0.0424   0.0199   1.0000
  17.750   1.0428   0.15130   0.14790  -0.0509   0.0205   1.0000
  18.000   1.0039   0.16745   0.16414  -0.0608   0.0213   1.0000
  18.250   0.9155   0.21004   0.20656  -0.0808   0.0271   1.0000
  18.500   0.9224   0.21369   0.21021  -0.0821   0.0279   1.0000
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