Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.63 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1012-il-1000000-n5.txt
Download as CSV file: xf-hq1012-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/12 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.9227   0.11773   0.11541  -0.0097   1.0000   0.0038
 -17.250  -0.9919   0.09980   0.09727  -0.0194   1.0000   0.0037
 -17.000  -1.0477   0.08502   0.08228  -0.0275   1.0000   0.0035
 -16.750  -1.0838   0.07397   0.07104  -0.0339   1.0000   0.0034
 -16.500  -1.1105   0.06516   0.06206  -0.0393   1.0000   0.0034
 -16.250  -1.1380   0.05690   0.05362  -0.0445   1.0000   0.0035
 -16.000  -1.1525   0.05130   0.04788  -0.0476   1.0000   0.0034
 -15.750  -1.1682   0.04601   0.04244  -0.0503   1.0000   0.0034
 -15.500  -1.1726   0.04251   0.03883  -0.0518   1.0000   0.0034
 -15.250  -1.1845   0.03840   0.03457  -0.0531   1.0000   0.0035
 -15.000  -1.1878   0.03551   0.03156  -0.0536   1.0000   0.0035
 -14.750  -1.1895   0.03296   0.02890  -0.0537   1.0000   0.0035
 -14.500  -1.1898   0.03073   0.02656  -0.0534   1.0000   0.0036
 -14.250  -1.1854   0.02905   0.02480  -0.0528   1.0000   0.0038
 -14.000  -1.1806   0.02753   0.02320  -0.0519   1.0000   0.0038
 -13.750  -1.1759   0.02612   0.02171  -0.0507   1.0000   0.0039
 -13.500  -1.1723   0.02479   0.02027  -0.0490   1.0000   0.0040
 -13.250  -1.1650   0.02385   0.01926  -0.0471   1.0000   0.0040
 -13.000  -1.1588   0.02295   0.01827  -0.0446   1.0000   0.0041
 -12.750  -1.1491   0.02219   0.01744  -0.0424   1.0000   0.0043
 -12.500  -1.1358   0.02139   0.01656  -0.0409   1.0000   0.0044
 -12.250  -1.1208   0.02063   0.01574  -0.0394   1.0000   0.0045
 -12.000  -1.1049   0.01990   0.01493  -0.0381   1.0000   0.0046
 -11.750  -1.0876   0.01923   0.01419  -0.0369   1.0000   0.0048
 -11.500  -1.0694   0.01861   0.01351  -0.0357   1.0000   0.0049
 -11.250  -1.0503   0.01806   0.01289  -0.0347   1.0000   0.0050
 -11.000  -1.0326   0.01735   0.01212  -0.0334   1.0000   0.0053
 -10.750  -1.0143   0.01669   0.01139  -0.0321   1.0000   0.0056
 -10.500  -0.9951   0.01613   0.01080  -0.0310   1.0000   0.0059
 -10.250  -0.9706   0.01558   0.01021  -0.0308   0.9964   0.0062
 -10.000  -0.9398   0.01505   0.00963  -0.0320   0.9874   0.0066
  -9.750  -0.9069   0.01453   0.00906  -0.0336   0.9783   0.0070
  -9.500  -0.8729   0.01405   0.00852  -0.0354   0.9676   0.0074
  -9.250  -0.8415   0.01346   0.00787  -0.0366   0.9514   0.0081
  -8.750  -0.7901   0.01271   0.00695  -0.0363   0.9069   0.0095
  -8.500  -0.7663   0.01241   0.00656  -0.0356   0.8913   0.0102
  -8.250  -0.7425   0.01208   0.00616  -0.0350   0.8776   0.0115
  -8.000  -0.7184   0.01176   0.00579  -0.0344   0.8656   0.0132
  -7.500  -0.6689   0.01116   0.00511  -0.0335   0.8453   0.0188
  -7.250  -0.6438   0.01087   0.00482  -0.0332   0.8366   0.0228
  -7.000  -0.6179   0.01066   0.00456  -0.0329   0.8280   0.0251
  -6.750  -0.5920   0.01041   0.00429  -0.0326   0.8200   0.0285
  -6.500  -0.5660   0.01019   0.00404  -0.0323   0.8119   0.0319
  -6.250  -0.5394   0.01000   0.00382  -0.0322   0.8043   0.0341
  -6.000  -0.5132   0.00979   0.00358  -0.0319   0.7968   0.0382
  -5.750  -0.4864   0.00959   0.00338  -0.0318   0.7895   0.0417
  -5.500  -0.4598   0.00941   0.00316  -0.0316   0.7824   0.0468
  -5.250  -0.4330   0.00920   0.00297  -0.0314   0.7758   0.0541
  -5.000  -0.4063   0.00901   0.00278  -0.0313   0.7687   0.0620
  -4.750  -0.3792   0.00883   0.00260  -0.0312   0.7623   0.0696
  -4.500  -0.3522   0.00865   0.00243  -0.0311   0.7555   0.0794
  -4.250  -0.3252   0.00847   0.00226  -0.0309   0.7493   0.0914
  -4.000  -0.2981   0.00828   0.00211  -0.0309   0.7425   0.1060
  -3.750  -0.2712   0.00809   0.00196  -0.0307   0.7360   0.1246
  -3.500  -0.2442   0.00787   0.00181  -0.0307   0.7287   0.1497
  -3.250  -0.2174   0.00767   0.00168  -0.0305   0.7214   0.1773
  -3.000  -0.1901   0.00748   0.00156  -0.0305   0.7140   0.2031
  -2.750  -0.1632   0.00728   0.00144  -0.0304   0.7074   0.2371
  -2.500  -0.1361   0.00705   0.00133  -0.0303   0.7012   0.2716
  -2.250  -0.1096   0.00680   0.00121  -0.0302   0.6931   0.3174
  -2.000  -0.0832   0.00651   0.00110  -0.0300   0.6831   0.3805
  -1.750  -0.0563   0.00632   0.00102  -0.0299   0.6729   0.4248
  -1.500  -0.0298   0.00610   0.00096  -0.0298   0.6641   0.4795
  -1.250  -0.0023   0.00597   0.00092  -0.0297   0.6557   0.5180
  -1.000   0.0251   0.00587   0.00091  -0.0296   0.6477   0.5523
  -0.750   0.0532   0.00583   0.00090  -0.0296   0.6389   0.5723
  -0.500   0.0813   0.00583   0.00089  -0.0296   0.6288   0.5839
  -0.250   0.1093   0.00584   0.00088  -0.0296   0.6186   0.5959
   0.000   0.1375   0.00585   0.00089  -0.0296   0.6072   0.6082
   0.250   0.1655   0.00587   0.00090  -0.0296   0.5933   0.6198
   0.500   0.1935   0.00590   0.00091  -0.0296   0.5801   0.6304
   0.750   0.2215   0.00593   0.00094  -0.0296   0.5681   0.6399
   1.000   0.2494   0.00599   0.00097  -0.0295   0.5527   0.6493
   1.250   0.2769   0.00606   0.00101  -0.0295   0.5341   0.6582
   1.500   0.3045   0.00615   0.00105  -0.0294   0.5148   0.6672
   1.750   0.3317   0.00628   0.00111  -0.0293   0.4897   0.6756
   2.000   0.3585   0.00644   0.00119  -0.0291   0.4599   0.6816
   2.250   0.3849   0.00667   0.00129  -0.0289   0.4216   0.6879
   2.500   0.4111   0.00691   0.00140  -0.0286   0.3850   0.6938
   2.750   0.4371   0.00716   0.00153  -0.0284   0.3453   0.7004
   3.000   0.4624   0.00751   0.00169  -0.0280   0.2983   0.7071
   3.250   0.4879   0.00780   0.00186  -0.0277   0.2628   0.7142
   3.500   0.5147   0.00798   0.00199  -0.0275   0.2460   0.7215
   3.750   0.5417   0.00811   0.00212  -0.0274   0.2355   0.7284
   4.000   0.5687   0.00825   0.00225  -0.0273   0.2249   0.7357
   4.250   0.5956   0.00839   0.00238  -0.0271   0.2140   0.7424
   4.500   0.6221   0.00858   0.00253  -0.0270   0.1987   0.7500
   4.750   0.6482   0.00877   0.00270  -0.0267   0.1824   0.7571
   5.000   0.6744   0.00897   0.00286  -0.0265   0.1671   0.7649
   5.250   0.7002   0.00919   0.00306  -0.0262   0.1512   0.7725
   5.500   0.7254   0.00947   0.00328  -0.0258   0.1312   0.7810
   5.750   0.7501   0.00976   0.00352  -0.0253   0.1140   0.7896
   6.000   0.7752   0.01002   0.00376  -0.0250   0.1013   0.7986
   6.250   0.7999   0.01030   0.00401  -0.0245   0.0881   0.8086
   6.500   0.8242   0.01059   0.00429  -0.0240   0.0759   0.8190
   6.750   0.8487   0.01085   0.00456  -0.0234   0.0665   0.8304
   7.000   0.8725   0.01114   0.00484  -0.0228   0.0571   0.8434
   7.250   0.8959   0.01142   0.00514  -0.0221   0.0497   0.8587
   7.500   0.9195   0.01160   0.00541  -0.0214   0.0460   0.8797
   7.750   0.9408   0.01184   0.00574  -0.0202   0.0390   0.9190
   8.000   0.9821   0.01218   0.00613  -0.0235   0.0340   1.0000
   8.250   1.0053   0.01255   0.00648  -0.0228   0.0293   1.0000
   8.500   1.0286   0.01290   0.00682  -0.0222   0.0258   1.0000
   8.750   1.0511   0.01330   0.00722  -0.0215   0.0219   1.0000
   9.000   1.0735   0.01371   0.00762  -0.0207   0.0184   1.0000
   9.250   1.0953   0.01415   0.00804  -0.0199   0.0156   1.0000
   9.500   1.1164   0.01463   0.00851  -0.0190   0.0129   1.0000
   9.750   1.1376   0.01508   0.00898  -0.0181   0.0107   1.0000
  10.000   1.1576   0.01560   0.00950  -0.0171   0.0086   1.0000
  10.250   1.1772   0.01612   0.01005  -0.0160   0.0068   1.0000
  10.500   1.1963   0.01666   0.01061  -0.0148   0.0057   1.0000
  10.750   1.2148   0.01720   0.01118  -0.0136   0.0051   1.0000
  11.000   1.2317   0.01781   0.01181  -0.0121   0.0044   1.0000
  11.250   1.2476   0.01837   0.01242  -0.0105   0.0041   1.0000
  11.500   1.2610   0.01895   0.01306  -0.0084   0.0039   1.0000
  11.750   1.2740   0.01954   0.01370  -0.0063   0.0038   1.0000
  12.000   1.2856   0.02023   0.01445  -0.0042   0.0035   1.0000
  12.250   1.2975   0.02093   0.01522  -0.0023   0.0034   1.0000
  12.500   1.3076   0.02178   0.01613  -0.0003   0.0033   1.0000
  12.750   1.3176   0.02267   0.01709   0.0016   0.0032   1.0000
  13.000   1.3267   0.02367   0.01816   0.0033   0.0031   1.0000
  13.250   1.3347   0.02479   0.01934   0.0050   0.0030   1.0000
  13.500   1.3419   0.02602   0.02066   0.0066   0.0029   1.0000
  13.750   1.3478   0.02740   0.02213   0.0081   0.0028   1.0000
  14.000   1.3497   0.02919   0.02402   0.0096   0.0027   1.0000
  14.250   1.3567   0.03062   0.02553   0.0106   0.0026   1.0000
  14.500   1.3606   0.03239   0.02739   0.0115   0.0026   1.0000
  14.750   1.3649   0.03420   0.02929   0.0123   0.0026   1.0000
  15.000   1.3657   0.03641   0.03162   0.0129   0.0026   1.0000
  15.250   1.3678   0.03860   0.03391   0.0133   0.0025   1.0000
  15.500   1.3689   0.04099   0.03639   0.0134   0.0025   1.0000
  15.750   1.3672   0.04379   0.03929   0.0134   0.0024   1.0000
  16.000   1.3638   0.04691   0.04252   0.0130   0.0025   1.0000
  16.250   1.3572   0.05057   0.04631   0.0123   0.0024   1.0000
  16.500   1.3498   0.05458   0.05044   0.0111   0.0024   1.0000
  16.750   1.3430   0.05875   0.05472   0.0097   0.0024   1.0000
  17.000   1.3316   0.06385   0.05995   0.0076   0.0023   1.0000
  17.250   1.3191   0.06941   0.06564   0.0050   0.0024   1.0000
  17.500   1.3024   0.07597   0.07235   0.0017   0.0023   1.0000
  17.750   1.2859   0.08282   0.07933  -0.0019   0.0024   1.0000
  18.000   1.2577   0.09214   0.08883  -0.0069   0.0023   1.0000
  18.250   1.2308   0.10160   0.09846  -0.0122   0.0023   1.0000
  18.500   1.1997   0.11209   0.10910  -0.0180   0.0024   1.0000
  18.750   1.1708   0.12239   0.11954  -0.0238   0.0024   1.0000
<< Back to HQ 1.0/12 AIRFOIL (hq1012-il)

Polar data table (+)

Polar graphs


<< Back to HQ 1.0/12 AIRFOIL (hq1012-il)