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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 100,000
Max Cl/Cd: 59.94 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq309-il-100000-n5.txt
Download as CSV file: xf-hq309-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2994   0.07942   0.07504  -0.0381   1.0000   0.0286
  -8.000  -0.3030   0.07628   0.07197  -0.0368   1.0000   0.0272
  -7.500  -0.3870   0.08264   0.07814  -0.0359   1.0000   0.0276
  -7.250  -0.3977   0.08027   0.07587  -0.0345   1.0000   0.0266
  -7.000  -0.4075   0.07742   0.07312  -0.0343   1.0000   0.0258
  -6.750  -0.4162   0.07427   0.07003  -0.0350   1.0000   0.0250
  -6.500  -0.4227   0.07055   0.06634  -0.0365   1.0000   0.0240
  -6.000  -0.3645   0.05396   0.04911  -0.0570   0.9860   0.0193
  -5.750  -0.3410   0.04856   0.04344  -0.0616   0.9797   0.0189
  -5.500  -0.3121   0.04328   0.03778  -0.0663   0.9746   0.0187
  -5.250  -0.2814   0.03902   0.03292  -0.0693   0.9689   0.0196
  -5.000  -0.2552   0.03521   0.02889  -0.0724   0.9637   0.0217
  -4.750  -0.2211   0.03186   0.02505  -0.0751   0.9602   0.0225
  -4.500  -0.1915   0.02864   0.02126  -0.0761   0.9547   0.0226
  -4.250  -0.1585   0.02598   0.01809  -0.0774   0.9503   0.0232
  -4.000  -0.1232   0.02375   0.01542  -0.0788   0.9473   0.0242
  -3.750  -0.0923   0.02202   0.01333  -0.0792   0.9425   0.0258
  -3.500  -0.0610   0.02078   0.01184  -0.0797   0.9376   0.0292
  -3.250  -0.0270   0.01955   0.01058  -0.0811   0.9342   0.0353
  -3.000   0.0038   0.01854   0.00940  -0.0815   0.9292   0.0423
  -2.750   0.0342   0.01769   0.00860  -0.0823   0.9238   0.0625
  -2.500   0.0688   0.01702   0.00792  -0.0839   0.9200   0.0981
  -2.250   0.0974   0.01627   0.00734  -0.0843   0.9138   0.1475
  -2.000   0.1245   0.01472   0.00717  -0.0850   0.9088   0.5061
  -1.750   0.1542   0.01444   0.00723  -0.0846   0.9049   0.6601
  -1.500   0.1744   0.01441   0.00730  -0.0824   0.8966   0.7351
  -1.250   0.1979   0.01421   0.00722  -0.0801   0.8918   0.8112
  -1.000   0.2168   0.01405   0.00710  -0.0775   0.8835   0.8590
  -0.750   0.2502   0.01387   0.00682  -0.0782   0.8787   0.8836
  -0.500   0.2829   0.01376   0.00664  -0.0791   0.8713   0.9110
  -0.250   0.3276   0.01359   0.00635  -0.0824   0.8661   0.9525
   0.000   0.3626   0.01355   0.00619  -0.0841   0.8579   1.0000
   0.250   0.3958   0.01351   0.00602  -0.0852   0.8511   1.0000
   0.500   0.4235   0.01358   0.00599  -0.0853   0.8416   1.0000
   0.750   0.4550   0.01357   0.00589  -0.0860   0.8343   1.0000
   1.000   0.4834   0.01362   0.00587  -0.0861   0.8251   1.0000
   1.250   0.5113   0.01365   0.00586  -0.0860   0.8147   1.0000
   1.500   0.5399   0.01362   0.00579  -0.0859   0.8030   1.0000
   1.750   0.5682   0.01358   0.00570  -0.0857   0.7904   1.0000
   2.000   0.5964   0.01357   0.00566  -0.0855   0.7781   1.0000
   2.250   0.6245   0.01358   0.00568  -0.0853   0.7659   1.0000
   2.500   0.6519   0.01361   0.00570  -0.0850   0.7524   1.0000
   2.750   0.6785   0.01366   0.00575  -0.0845   0.7368   1.0000
   3.000   0.7049   0.01370   0.00580  -0.0839   0.7194   1.0000
   3.250   0.7319   0.01374   0.00583  -0.0834   0.7012   1.0000
   3.500   0.7581   0.01382   0.00596  -0.0829   0.6815   1.0000
   3.750   0.7843   0.01392   0.00607  -0.0822   0.6602   1.0000
   4.000   0.8098   0.01406   0.00621  -0.0815   0.6360   1.0000
   4.250   0.8349   0.01423   0.00637  -0.0808   0.6086   1.0000
   4.500   0.8596   0.01445   0.00660  -0.0799   0.5767   1.0000
   4.750   0.8834   0.01474   0.00682  -0.0789   0.5399   1.0000
   5.000   0.9063   0.01512   0.00709  -0.0778   0.4996   1.0000
   5.250   0.9282   0.01561   0.00744  -0.0767   0.4576   1.0000
   5.500   0.9493   0.01618   0.00788  -0.0755   0.4168   1.0000
   5.750   0.9699   0.01683   0.00840  -0.0743   0.3776   1.0000
   6.000   0.9901   0.01752   0.00903  -0.0731   0.3406   1.0000
   6.250   1.0100   0.01824   0.00966  -0.0719   0.3049   1.0000
   6.500   1.0291   0.01902   0.01033  -0.0707   0.2722   1.0000
   6.750   1.0485   0.01980   0.01106  -0.0695   0.2410   1.0000
   7.000   1.0678   0.02059   0.01181  -0.0684   0.2113   1.0000
   7.250   1.0868   0.02140   0.01260  -0.0672   0.1845   1.0000
   7.500   1.1049   0.02230   0.01344  -0.0660   0.1545   1.0000
   7.750   1.1210   0.02339   0.01438  -0.0647   0.1141   1.0000
   8.000   1.1366   0.02459   0.01539  -0.0634   0.0818   1.0000
   8.250   1.1528   0.02574   0.01654  -0.0620   0.0628   1.0000
   8.500   1.1666   0.02714   0.01790  -0.0603   0.0447   1.0000
   8.750   1.1791   0.02867   0.01944  -0.0585   0.0293   1.0000
   9.000   1.1882   0.03050   0.02136  -0.0561   0.0216   1.0000
   9.250   1.1956   0.03225   0.02328  -0.0535   0.0179   1.0000
   9.500   1.1981   0.03427   0.02542  -0.0505   0.0157   1.0000
   9.750   1.2046   0.03596   0.02735  -0.0481   0.0140   1.0000
  10.000   1.2103   0.03772   0.02930  -0.0458   0.0124   1.0000
  10.250   1.2149   0.03959   0.03134  -0.0438   0.0112   1.0000
  10.500   1.2171   0.04172   0.03365  -0.0417   0.0105   1.0000
  10.750   1.2163   0.04425   0.03645  -0.0398   0.0101   1.0000
  11.000   1.2136   0.04715   0.03956  -0.0380   0.0098   1.0000
  11.250   1.2109   0.05029   0.04290  -0.0365   0.0096   1.0000
  11.500   1.2096   0.05340   0.04626  -0.0353   0.0094   1.0000
  11.750   1.2066   0.05680   0.04992  -0.0345   0.0093   1.0000
  12.000   1.2012   0.06064   0.05404  -0.0340   0.0092   1.0000
  12.250   1.1940   0.06478   0.05843  -0.0340   0.0091   1.0000
  12.500   1.1843   0.06945   0.06338  -0.0345   0.0090   1.0000
  12.750   1.1729   0.07456   0.06874  -0.0358   0.0090   1.0000
  13.000   1.1595   0.08029   0.07472  -0.0378   0.0090   1.0000
  13.250   1.1447   0.08663   0.08129  -0.0407   0.0090   1.0000
  13.500   1.1295   0.09350   0.08836  -0.0443   0.0091   1.0000
  13.750   1.1129   0.10125   0.09632  -0.0489   0.0091   1.0000
  14.000   1.0962   0.10965   0.10489  -0.0541   0.0092   1.0000
  14.250   1.0798   0.11864   0.11403  -0.0597   0.0093   1.0000
  14.500   1.0636   0.12814   0.12365  -0.0657   0.0094   1.0000
  14.750   1.0481   0.13797   0.13358  -0.0717   0.0095   1.0000
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