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HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il)
Reynolds number: 100,000
Max Cl/Cd: 55.97 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3513-il-100000-n5.txt
Download as CSV file: xf-hq3513-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/13 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3681   0.09327   0.08853  -0.0519   1.0000   0.0270
  -9.750  -0.3816   0.08992   0.08527  -0.0512   1.0000   0.0270
  -9.500  -0.3985   0.08666   0.08211  -0.0502   1.0000   0.0270
  -9.250  -0.4049   0.08108   0.07659  -0.0538   0.9965   0.0269
  -9.000  -0.4072   0.07177   0.06726  -0.0635   0.9882   0.0267
  -8.750  -0.4176   0.06317   0.05855  -0.0741   0.9763   0.0263
  -8.500  -0.4258   0.05565   0.05074  -0.0826   0.9632   0.0262
  -8.250  -0.4256   0.04930   0.04396  -0.0878   0.9536   0.0262
  -8.000  -0.4193   0.04364   0.03775  -0.0910   0.9450   0.0264
  -7.750  -0.4090   0.03884   0.03229  -0.0924   0.9370   0.0268
  -7.500  -0.3892   0.03500   0.02787  -0.0938   0.9312   0.0276
  -7.250  -0.3600   0.03280   0.02544  -0.0958   0.9280   0.0286
  -7.000  -0.3413   0.03120   0.02361  -0.0952   0.9201   0.0299
  -6.750  -0.3128   0.02917   0.02120  -0.0962   0.9160   0.0322
  -6.500  -0.2826   0.02733   0.01898  -0.0972   0.9125   0.0358
  -6.250  -0.2610   0.02660   0.01821  -0.0967   0.9052   0.0392
  -6.000  -0.2303   0.02528   0.01657  -0.0974   0.9013   0.0449
  -5.750  -0.1987   0.02453   0.01580  -0.0988   0.8980   0.0520
  -5.500  -0.1779   0.02379   0.01490  -0.0978   0.8905   0.0582
  -5.000  -0.1172   0.02220   0.01317  -0.0992   0.8828   0.0724
  -4.750  -0.0961   0.02165   0.01258  -0.0981   0.8755   0.0772
  -4.500  -0.0664   0.02099   0.01180  -0.0984   0.8714   0.0836
  -4.250  -0.0388   0.02038   0.01120  -0.0986   0.8669   0.0915
  -4.000  -0.0161   0.01994   0.01072  -0.0978   0.8602   0.0990
  -3.750   0.0136   0.01940   0.01012  -0.0983   0.8561   0.1115
  -3.500   0.0395   0.01887   0.00969  -0.0982   0.8510   0.1333
  -3.250   0.0629   0.01830   0.00935  -0.0978   0.8447   0.1821
  -3.000   0.0892   0.01713   0.00896  -0.0983   0.8406   0.3495
  -2.750   0.1097   0.01680   0.00918  -0.0969   0.8345   0.5046
  -2.500   0.1342   0.01682   0.00929  -0.0958   0.8288   0.5722
  -2.250   0.1639   0.01683   0.00926  -0.0956   0.8250   0.6154
  -2.000   0.1853   0.01702   0.00944  -0.0941   0.8180   0.6472
  -1.750   0.2100   0.01716   0.00957  -0.0927   0.8127   0.6838
  -1.500   0.2376   0.01722   0.00961  -0.0918   0.8091   0.7156
  -1.250   0.2562   0.01741   0.00978  -0.0897   0.8009   0.7352
  -1.000   0.2851   0.01734   0.00962  -0.0896   0.7963   0.7492
  -0.750   0.3101   0.01733   0.00956  -0.0888   0.7900   0.7579
  -0.500   0.3368   0.01730   0.00945  -0.0886   0.7837   0.7669
  -0.250   0.3685   0.01714   0.00920  -0.0890   0.7797   0.7754
   0.000   0.3899   0.01722   0.00926  -0.0878   0.7714   0.7842
   0.250   0.4205   0.01709   0.00906  -0.0881   0.7662   0.7935
   0.500   0.4443   0.01707   0.00902  -0.0872   0.7579   0.8022
   0.750   0.4750   0.01687   0.00875  -0.0874   0.7511   0.8116
   1.000   0.4990   0.01681   0.00867  -0.0865   0.7411   0.8216
   1.250   0.5291   0.01656   0.00838  -0.0864   0.7333   0.8312
   1.500   0.5535   0.01648   0.00830  -0.0856   0.7230   0.8424
   1.750   0.5788   0.01638   0.00820  -0.0849   0.7128   0.8543
   2.000   0.6077   0.01616   0.00797  -0.0846   0.7040   0.8668
   2.250   0.6317   0.01612   0.00797  -0.0838   0.6935   0.8821
   2.500   0.6593   0.01606   0.00795  -0.0836   0.6840   0.9008
   2.750   0.6951   0.01590   0.00783  -0.0849   0.6753   0.9246
   3.000   0.7310   0.01590   0.00786  -0.0867   0.6632   1.0000
   3.250   0.7576   0.01600   0.00794  -0.0867   0.6515   1.0000
   3.500   0.7847   0.01609   0.00801  -0.0868   0.6396   1.0000
   3.750   0.8115   0.01618   0.00807  -0.0867   0.6267   1.0000
   4.000   0.8373   0.01630   0.00816  -0.0864   0.6122   1.0000
   4.250   0.8623   0.01643   0.00829  -0.0859   0.5965   1.0000
   4.500   0.8867   0.01658   0.00842  -0.0853   0.5794   1.0000
   4.750   0.9109   0.01675   0.00854  -0.0846   0.5606   1.0000
   5.000   0.9346   0.01693   0.00867  -0.0839   0.5399   1.0000
   5.250   0.9570   0.01719   0.00887  -0.0829   0.5162   1.0000
   5.500   0.9788   0.01749   0.00908  -0.0818   0.4913   1.0000
   5.750   0.9996   0.01786   0.00932  -0.0806   0.4655   1.0000
   6.000   1.0191   0.01832   0.00967  -0.0793   0.4395   1.0000
   6.250   1.0378   0.01883   0.01007  -0.0778   0.4149   1.0000
   6.500   1.0558   0.01940   0.01052  -0.0764   0.3930   1.0000
   6.750   1.0738   0.01999   0.01103  -0.0749   0.3727   1.0000
   7.000   1.0916   0.02059   0.01158  -0.0735   0.3550   1.0000
   7.250   1.1093   0.02121   0.01215  -0.0721   0.3395   1.0000
   7.500   1.1266   0.02182   0.01273  -0.0706   0.3260   1.0000
   7.750   1.1434   0.02245   0.01333  -0.0691   0.3140   1.0000
   8.250   1.1775   0.02378   0.01467  -0.0662   0.2931   1.0000
   8.500   1.1946   0.02447   0.01537  -0.0649   0.2836   1.0000
   8.750   1.2111   0.02522   0.01610  -0.0635   0.2746   1.0000
   9.000   1.2274   0.02593   0.01690  -0.0621   0.2651   1.0000
   9.250   1.2433   0.02672   0.01772  -0.0607   0.2565   1.0000
   9.500   1.2581   0.02750   0.01858  -0.0592   0.2474   1.0000
   9.750   1.2729   0.02831   0.01948  -0.0577   0.2389   1.0000
  10.000   1.2861   0.02917   0.02039  -0.0562   0.2305   1.0000
  10.250   1.2995   0.03003   0.02141  -0.0546   0.2219   1.0000
  10.500   1.3111   0.03099   0.02239  -0.0530   0.2141   1.0000
  10.750   1.3225   0.03195   0.02356  -0.0514   0.2051   1.0000
  11.000   1.3326   0.03301   0.02471  -0.0498   0.1971   1.0000
  11.250   1.3415   0.03414   0.02597  -0.0482   0.1883   1.0000
  11.500   1.3500   0.03535   0.02732  -0.0466   0.1793   1.0000
  11.750   1.3560   0.03671   0.02873  -0.0450   0.1712   1.0000
  12.000   1.3627   0.03814   0.03032  -0.0435   0.1615   1.0000
  12.250   1.3670   0.03975   0.03203  -0.0420   0.1518   1.0000
  12.500   1.3693   0.04157   0.03390  -0.0407   0.1428   1.0000
  12.750   1.3709   0.04356   0.03600  -0.0394   0.1329   1.0000
  13.000   1.3725   0.04569   0.03822  -0.0384   0.1232   1.0000
  13.250   1.3713   0.04813   0.04071  -0.0375   0.1135   1.0000
  13.750   1.3665   0.05365   0.04637  -0.0362   0.0957   1.0000
  14.000   1.3632   0.05672   0.04953  -0.0359   0.0881   1.0000
  14.250   1.3577   0.06017   0.05306  -0.0359   0.0814   1.0000
  14.500   1.3530   0.06374   0.05676  -0.0361   0.0742   1.0000
  14.750   1.3432   0.06809   0.06117  -0.0367   0.0686   1.0000
  15.000   1.3364   0.07230   0.06555  -0.0375   0.0624   1.0000
  15.250   1.3233   0.07760   0.07092  -0.0389   0.0575   1.0000
  15.500   1.3134   0.08269   0.07619  -0.0405   0.0526   1.0000
  15.750   1.2994   0.08867   0.08229  -0.0426   0.0488   1.0000
  16.000   1.2832   0.09526   0.08899  -0.0453   0.0465   1.0000
  16.250   1.2705   0.10155   0.09548  -0.0480   0.0430   1.0000
  16.500   1.2558   0.10834   0.10242  -0.0511   0.0405   1.0000
  16.750   1.2397   0.11558   0.10976  -0.0546   0.0382   1.0000
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