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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 500,000
Max Cl/Cd: 102.61 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2511-il-500000.txt
Download as CSV file: xf-hq2511-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/11 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3216   0.09603   0.09389  -0.0392   1.0000   0.0223
 -10.500  -0.4227   0.09738   0.09510  -0.0399   1.0000   0.0214
 -10.250  -0.4231   0.09346   0.09120  -0.0410   1.0000   0.0216
 -10.000  -0.4189   0.09110   0.08886  -0.0410   1.0000   0.0220
  -9.750  -0.4192   0.08732   0.08510  -0.0424   1.0000   0.0222
  -9.500  -0.4183   0.08412   0.08192  -0.0434   1.0000   0.0225
  -9.250  -0.4215   0.08004   0.07788  -0.0451   1.0000   0.0228
  -9.000  -0.4259   0.07601   0.07390  -0.0468   1.0000   0.0231
  -8.750  -0.4382   0.07077   0.06872  -0.0495   1.0000   0.0230
  -8.500  -0.4776   0.02663   0.02399  -0.0757   0.9836   0.0166
  -8.250  -0.5354   0.02631   0.02214  -0.0773   0.9773   0.0123
  -8.000  -0.5052   0.02376   0.01922  -0.0795   0.9740   0.0122
  -7.750  -0.4759   0.02062   0.01566  -0.0815   0.9710   0.0124
  -7.500  -0.4492   0.01873   0.01350  -0.0821   0.9648   0.0125
  -7.250  -0.4193   0.01735   0.01190  -0.0830   0.9598   0.0124
  -7.000  -0.3906   0.01612   0.01050  -0.0835   0.9544   0.0123
  -6.750  -0.3657   0.01510   0.00936  -0.0831   0.9465   0.0123
  -6.500  -0.3404   0.01407   0.00821  -0.0828   0.9400   0.0123
  -6.250  -0.3171   0.01320   0.00725  -0.0821   0.9316   0.0124
  -6.000  -0.2924   0.01252   0.00646  -0.0816   0.9244   0.0126
  -5.750  -0.2679   0.01191   0.00578  -0.0810   0.9165   0.0131
  -5.500  -0.2423   0.01146   0.00525  -0.0805   0.9095   0.0136
  -5.250  -0.2165   0.01107   0.00479  -0.0801   0.9021   0.0146
  -5.000  -0.1902   0.01071   0.00435  -0.0797   0.8950   0.0164
  -4.750  -0.1645   0.01029   0.00394  -0.0792   0.8872   0.0246
  -4.500  -0.1380   0.01002   0.00371  -0.0789   0.8797   0.0389
  -4.250  -0.1109   0.00989   0.00352  -0.0787   0.8725   0.0461
  -4.000  -0.0839   0.00969   0.00333  -0.0786   0.8660   0.0546
  -3.750  -0.0568   0.00953   0.00314  -0.0784   0.8590   0.0626
  -3.500  -0.0295   0.00937   0.00297  -0.0783   0.8528   0.0741
  -3.250  -0.0026   0.00913   0.00278  -0.0782   0.8456   0.0921
  -3.000   0.0241   0.00880   0.00256  -0.0781   0.8396   0.1345
  -2.750   0.0494   0.00817   0.00236  -0.0780   0.8322   0.2533
  -2.500   0.0740   0.00741   0.00217  -0.0779   0.8260   0.4336
  -2.250   0.0994   0.00702   0.00216  -0.0776   0.8190   0.5461
  -2.000   0.1262   0.00692   0.00218  -0.0772   0.8129   0.6056
  -1.750   0.1540   0.00692   0.00218  -0.0771   0.8072   0.6319
  -1.500   0.1814   0.00691   0.00218  -0.0768   0.8003   0.6548
  -1.250   0.2091   0.00692   0.00215  -0.0766   0.7935   0.6713
  -1.000   0.2366   0.00692   0.00215  -0.0764   0.7857   0.6875
  -0.750   0.2642   0.00695   0.00214  -0.0761   0.7794   0.7040
  -0.500   0.2913   0.00696   0.00217  -0.0758   0.7721   0.7218
  -0.250   0.3189   0.00698   0.00216  -0.0756   0.7655   0.7343
   0.000   0.3462   0.00695   0.00216  -0.0753   0.7570   0.7432
   0.250   0.3739   0.00696   0.00213  -0.0752   0.7485   0.7519
   0.500   0.4013   0.00696   0.00212  -0.0750   0.7401   0.7603
   0.750   0.4288   0.00697   0.00213  -0.0748   0.7322   0.7690
   1.000   0.4563   0.00699   0.00213  -0.0746   0.7235   0.7778
   1.250   0.4837   0.00699   0.00216  -0.0744   0.7150   0.7855
   1.500   0.5114   0.00703   0.00217  -0.0743   0.7072   0.7938
   1.750   0.5385   0.00702   0.00221  -0.0741   0.6972   0.8015
   2.000   0.5656   0.00704   0.00223  -0.0739   0.6850   0.8105
   2.250   0.5919   0.00706   0.00224  -0.0735   0.6699   0.8193
   2.500   0.6183   0.00709   0.00226  -0.0730   0.6538   0.8289
   2.750   0.6445   0.00713   0.00231  -0.0727   0.6380   0.8401
   3.000   0.6702   0.00717   0.00236  -0.0721   0.6208   0.8530
   3.250   0.6952   0.00721   0.00242  -0.0715   0.6000   0.8684
   3.500   0.7185   0.00726   0.00249  -0.0704   0.5749   0.8906
   3.750   0.7425   0.00731   0.00256  -0.0694   0.5454   0.9357
   4.000   0.7778   0.00758   0.00268  -0.0713   0.5031   1.0000
   4.250   0.8021   0.00795   0.00287  -0.0708   0.4670   1.0000
   4.500   0.8267   0.00830   0.00310  -0.0704   0.4383   1.0000
   4.750   0.8513   0.00864   0.00333  -0.0700   0.4108   1.0000
   5.000   0.8757   0.00898   0.00356  -0.0695   0.3770   1.0000
   5.250   0.8987   0.00943   0.00383  -0.0688   0.3353   1.0000
   5.500   0.9206   0.00997   0.00417  -0.0680   0.2994   1.0000
   5.750   0.9432   0.01045   0.00451  -0.0673   0.2705   1.0000
   6.000   0.9663   0.01090   0.00484  -0.0667   0.2421   1.0000
   6.250   0.9892   0.01134   0.00517  -0.0660   0.2142   1.0000
   6.500   1.0119   0.01180   0.00552  -0.0654   0.1887   1.0000
   6.750   1.0341   0.01229   0.00590  -0.0646   0.1648   1.0000
   7.000   1.0562   0.01277   0.00629  -0.0638   0.1460   1.0000
   7.250   1.0780   0.01327   0.00673  -0.0630   0.1296   1.0000
   7.500   1.0996   0.01377   0.00715  -0.0622   0.1116   1.0000
   7.750   1.1197   0.01439   0.00764  -0.0612   0.0894   1.0000
   8.000   1.1300   0.01583   0.00862  -0.0588   0.0306   1.0000
   8.250   1.1471   0.01668   0.00948  -0.0571   0.0229   1.0000
   8.500   1.1633   0.01759   0.01047  -0.0553   0.0198   1.0000
   8.750   1.1817   0.01823   0.01118  -0.0540   0.0186   1.0000
   9.000   1.1983   0.01896   0.01199  -0.0524   0.0174   1.0000
   9.250   1.2115   0.01977   0.01287  -0.0502   0.0164   1.0000
   9.500   1.2214   0.02072   0.01389  -0.0475   0.0157   1.0000
   9.750   1.2257   0.02202   0.01529  -0.0442   0.0150   1.0000
  10.000   1.2263   0.02364   0.01703  -0.0407   0.0145   1.0000
  10.250   1.2373   0.02461   0.01809  -0.0387   0.0142   1.0000
  10.500   1.2482   0.02561   0.01918  -0.0368   0.0137   1.0000
  10.750   1.2576   0.02676   0.02041  -0.0349   0.0132   1.0000
  11.000   1.2653   0.02808   0.02182  -0.0329   0.0128   1.0000
  11.250   1.2728   0.02947   0.02329  -0.0312   0.0123   1.0000
  11.500   1.2786   0.03107   0.02499  -0.0294   0.0120   1.0000
  11.750   1.2842   0.03275   0.02675  -0.0278   0.0117   1.0000
  12.000   1.2886   0.03462   0.02870  -0.0262   0.0114   1.0000
  12.250   1.2907   0.03688   0.03104  -0.0247   0.0110   1.0000
  12.500   1.2937   0.03929   0.03355  -0.0233   0.0108   1.0000
  12.750   1.2963   0.04255   0.03694  -0.0218   0.0106   1.0000
  13.000   1.2982   0.04507   0.03962  -0.0208   0.0104   1.0000
  13.250   1.3000   0.04751   0.04223  -0.0199   0.0103   1.0000
  13.500   1.3000   0.05020   0.04508  -0.0193   0.0102   1.0000
  13.750   1.2987   0.05304   0.04809  -0.0189   0.0100   1.0000
  14.000   1.2961   0.05603   0.05125  -0.0189   0.0098   1.0000
  14.250   1.2911   0.05966   0.05505  -0.0190   0.0096   1.0000
  14.500   1.2851   0.06352   0.05908  -0.0196   0.0095   1.0000
  14.750   1.2785   0.06760   0.06332  -0.0205   0.0093   1.0000
  15.000   1.2707   0.07206   0.06795  -0.0219   0.0091   1.0000
  15.250   1.2596   0.07739   0.07346  -0.0238   0.0091   1.0000
  15.500   1.2485   0.08295   0.07919  -0.0262   0.0090   1.0000
  15.750   1.2353   0.08923   0.08565  -0.0292   0.0090   1.0000
  16.000   1.2210   0.09605   0.09266  -0.0328   0.0090   1.0000
  16.250   1.2049   0.10357   0.10035  -0.0370   0.0090   1.0000
  16.500   1.1862   0.11201   0.10898  -0.0420   0.0091   1.0000
  16.750   1.1694   0.12048   0.11762  -0.0473   0.0091   1.0000
  17.000   1.1501   0.12995   0.12726  -0.0533   0.0092   1.0000
  17.250   1.1283   0.14046   0.13794  -0.0600   0.0094   1.0000
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