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HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il)
Reynolds number: 100,000
Max Cl/Cd: 47.76 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3518-il-100000.txt
Download as CSV file: xf-hq3518-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/18 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3686   0.11704   0.11242  -0.0494   0.9846   0.1936
 -10.250  -0.6505   0.06910   0.06372  -0.0794   0.9672   0.1031
 -10.000  -0.6554   0.06520   0.05973  -0.0786   0.9597   0.1023
  -9.750  -0.6585   0.06052   0.05475  -0.0800   0.9537   0.1018
  -9.500  -0.6727   0.05762   0.05158  -0.0773   0.9463   0.1018
  -9.250  -0.6752   0.05428   0.04782  -0.0766   0.9408   0.1023
  -9.000  -0.6689   0.05118   0.04427  -0.0764   0.9363   0.1027
  -8.750  -0.6713   0.04909   0.04183  -0.0735   0.9297   0.1032
  -8.500  -0.6579   0.04626   0.03861  -0.0733   0.9254   0.1040
  -8.250  -0.6325   0.04379   0.03609  -0.0745   0.9227   0.1066
  -8.000  -0.6196   0.04269   0.03495  -0.0731   0.9188   0.1090
  -7.750  -0.6097   0.04145   0.03350  -0.0711   0.9141   0.1110
  -7.500  -0.5884   0.03993   0.03166  -0.0709   0.9099   0.1134
  -7.250  -0.5604   0.03871   0.02998  -0.0717   0.9067   0.1168
  -7.000  -0.5358   0.03721   0.02851  -0.0720   0.9040   0.1206
  -6.750  -0.5283   0.03663   0.02790  -0.0693   0.8997   0.1233
  -6.500  -0.5080   0.03589   0.02703  -0.0685   0.8956   0.1273
  -6.250  -0.4789   0.03500   0.02597  -0.0691   0.8919   0.1326
  -6.000  -0.4451   0.03430   0.02538  -0.0706   0.8892   0.1390
  -5.750  -0.4339   0.03398   0.02497  -0.0682   0.8840   0.1439
  -5.500  -0.4109   0.03337   0.02444  -0.0677   0.8777   0.1506
  -5.250  -0.3677   0.03281   0.02383  -0.0703   0.8726   0.1619
  -5.000  -0.3539   0.03247   0.02362  -0.0683   0.8645   0.1700
  -4.750  -0.3246   0.03199   0.02321  -0.0687   0.8585   0.1835
  -4.500  -0.2860   0.03138   0.02274  -0.0706   0.8549   0.2068
  -4.250  -0.2814   0.03118   0.02270  -0.0674   0.8486   0.2260
  -4.000  -0.2652   0.03046   0.02244  -0.0663   0.8433   0.2764
  -3.750  -0.2431   0.02939   0.02265  -0.0657   0.8392   0.4700
  -3.500  -0.2212   0.03008   0.02342  -0.0641   0.8340   0.5496
  -3.250  -0.2111   0.03079   0.02415  -0.0609   0.8265   0.5818
  -3.000  -0.1789   0.03163   0.02498  -0.0602   0.8216   0.6118
  -2.750  -0.1622   0.03244   0.02575  -0.0578   0.8149   0.6324
  -2.500  -0.1464   0.03315   0.02644  -0.0553   0.8078   0.6501
  -2.250  -0.1131   0.03379   0.02703  -0.0549   0.8034   0.6708
  -2.000  -0.1063   0.03451   0.02775  -0.0512   0.7953   0.6836
  -1.750  -0.0840   0.03498   0.02817  -0.0498   0.7889   0.6983
  -1.500  -0.0476   0.03529   0.02841  -0.0499   0.7852   0.7145
  -1.250  -0.0478   0.03594   0.02905  -0.0459   0.7748   0.7245
  -1.000  -0.0177   0.03613   0.02920  -0.0453   0.7696   0.7374
  -0.750  -0.0031   0.03654   0.02958  -0.0432   0.7612   0.7499
  -0.500   0.0178   0.03680   0.02980  -0.0416   0.7539   0.7627
  -0.250   0.0522   0.03677   0.02974  -0.0413   0.7504   0.7745
   0.000   0.0551   0.03736   0.03029  -0.0387   0.7386   0.7839
   0.250   0.0919   0.03705   0.02994  -0.0389   0.7339   0.7927
   0.500   0.1031   0.03750   0.03035  -0.0374   0.7228   0.8011
   0.750   0.1388   0.03705   0.02985  -0.0376   0.7172   0.8086
   1.000   0.1813   0.03659   0.02930  -0.0394   0.7127   0.8177
   1.250   0.1861   0.03694   0.02968  -0.0362   0.7006   0.8253
   1.500   0.2312   0.03631   0.02898  -0.0381   0.6976   0.8348
   1.750   0.2296   0.03706   0.02976  -0.0346   0.6847   0.8421
   2.000   0.2727   0.03639   0.02904  -0.0363   0.6812   0.8501
   2.250   0.3129   0.03579   0.02840  -0.0375   0.6779   0.8564
   2.500   0.3123   0.03680   0.02943  -0.0349   0.6651   0.8649
   2.750   0.3580   0.03589   0.02850  -0.0367   0.6626   0.8721
   3.000   0.3548   0.03714   0.02978  -0.0338   0.6495   0.8824
   3.250   0.3956   0.03638   0.02902  -0.0349   0.6463   0.8919
   3.500   0.4423   0.03531   0.02794  -0.0365   0.6446   0.9028
   3.750   0.4387   0.03678   0.02948  -0.0339   0.6304   0.9182
   4.000   0.4918   0.03547   0.02820  -0.0364   0.6284   0.9308
   4.250   0.5113   0.03662   0.02943  -0.0375   0.6153   0.9498
   4.500   0.5786   0.03512   0.02796  -0.0425   0.6131   0.9655
   4.750   0.6501   0.03325   0.02611  -0.0479   0.6121   0.9862
   5.000   0.7153   0.03141   0.02426  -0.0523   0.6108   1.0000
   5.250   0.7874   0.02935   0.02218  -0.0577   0.6089   1.0000
   5.500   0.7844   0.03007   0.02289  -0.0545   0.5950   1.0000
   5.750   0.8800   0.02693   0.01970  -0.0625   0.5927   1.0000
   6.000   0.8859   0.02715   0.01992  -0.0598   0.5787   1.0000
   6.250   0.9140   0.02672   0.01946  -0.0599   0.5668   1.0000
   6.500   0.9902   0.02478   0.01742  -0.0661   0.5591   1.0000
   6.750   1.0051   0.02492   0.01756  -0.0645   0.5451   1.0000
   7.000   1.0300   0.02482   0.01741  -0.0640   0.5315   1.0000
   7.250   1.0623   0.02455   0.01708  -0.0646   0.5179   1.0000
   7.500   1.0965   0.02434   0.01676  -0.0655   0.5038   1.0000
   7.750   1.1303   0.02427   0.01657  -0.0663   0.4892   1.0000
   8.000   1.1640   0.02437   0.01651  -0.0672   0.4743   1.0000
   8.250   1.1787   0.02489   0.01699  -0.0654   0.4596   1.0000
   8.500   1.1954   0.02547   0.01753  -0.0639   0.4455   1.0000
   8.750   1.2148   0.02604   0.01803  -0.0629   0.4318   1.0000
   9.000   1.2375   0.02657   0.01846  -0.0623   0.4182   1.0000
   9.250   1.2632   0.02705   0.01882  -0.0622   0.4046   1.0000
   9.500   1.2613   0.02795   0.01981  -0.0582   0.3924   1.0000
   9.750   1.2709   0.02872   0.02057  -0.0559   0.3801   1.0000
  10.000   1.2856   0.02932   0.02110  -0.0543   0.3678   1.0000
  10.250   1.2952   0.03004   0.02179  -0.0521   0.3557   1.0000
  10.500   1.3006   0.03101   0.02277  -0.0496   0.3436   1.0000
  10.750   1.3158   0.03184   0.02353  -0.0483   0.3320   1.0000
  11.000   1.3444   0.03252   0.02400  -0.0486   0.3201   1.0000
  11.250   1.3511   0.03379   0.02534  -0.0465   0.3098   1.0000
  11.500   1.3727   0.03490   0.02640  -0.0462   0.2996   1.0000
  11.750   1.3949   0.03592   0.02735  -0.0460   0.2899   1.0000
  12.000   1.4070   0.03734   0.02885  -0.0447   0.2822   1.0000
  12.250   1.4225   0.03855   0.03010  -0.0437   0.2748   1.0000
  12.500   1.4500   0.03973   0.03125  -0.0442   0.2678   1.0000
  12.750   1.4446   0.04144   0.03318  -0.0412   0.2624   1.0000
  13.000   1.4690   0.04241   0.03411  -0.0412   0.2560   1.0000
  13.250   1.4844   0.04390   0.03568  -0.0405   0.2508   1.0000
  13.500   1.4754   0.04597   0.03800  -0.0375   0.2468   1.0000
  13.750   1.4818   0.04755   0.03969  -0.0361   0.2421   1.0000
  14.000   1.5240   0.04813   0.04013  -0.0378   0.2363   1.0000
  14.250   1.5005   0.05085   0.04318  -0.0339   0.2332   1.0000
  14.500   1.4854   0.05351   0.04607  -0.0313   0.2294   1.0000
  14.750   1.4967   0.05467   0.04725  -0.0304   0.2244   1.0000
  15.000   1.5115   0.05583   0.04840  -0.0299   0.2190   1.0000
  15.250   1.4813   0.05970   0.05257  -0.0271   0.2159   1.0000
  15.500   1.4655   0.06281   0.05586  -0.0255   0.2119   1.0000
  15.750   1.5163   0.06110   0.05388  -0.0263   0.2047   1.0000
  16.000   1.4765   0.06630   0.05944  -0.0242   0.2026   1.0000
  16.250   1.4336   0.07256   0.06602  -0.0231   0.2004   1.0000
  16.500   0.8829   0.18771   0.18178  -0.0691   0.2532   1.0000
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