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HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il)
Reynolds number: 100,000
Max Cl/Cd: 55.08 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3013-il-100000-n5.txt
Download as CSV file: xf-hq3013-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/13 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4152   0.08581   0.08086  -0.0564   1.0000   0.0275
 -10.250  -0.4296   0.07931   0.07444  -0.0591   1.0000   0.0274
 -10.000  -0.4513   0.07178   0.06697  -0.0629   1.0000   0.0271
  -9.750  -0.4754   0.06662   0.06186  -0.0648   1.0000   0.0268
  -9.500  -0.5030   0.06337   0.05866  -0.0641   1.0000   0.0265
  -9.250  -0.5361   0.06164   0.05699  -0.0608   1.0000   0.0262
  -9.000  -0.5493   0.05427   0.04927  -0.0685   0.9867   0.0262
  -8.750  -0.5521   0.04727   0.04167  -0.0737   0.9750   0.0267
  -8.500  -0.5449   0.04178   0.03550  -0.0764   0.9659   0.0272
  -8.250  -0.5277   0.03771   0.03091  -0.0783   0.9591   0.0280
  -8.000  -0.5053   0.03554   0.02853  -0.0795   0.9530   0.0289
  -7.750  -0.4814   0.03346   0.02614  -0.0804   0.9468   0.0303
  -7.500  -0.4521   0.03103   0.02329  -0.0821   0.9430   0.0325
  -7.250  -0.4296   0.02911   0.02095  -0.0820   0.9361   0.0356
  -7.000  -0.4004   0.02814   0.01996  -0.0833   0.9313   0.0390
  -6.750  -0.3680   0.02662   0.01807  -0.0845   0.9280   0.0439
  -6.500  -0.3455   0.02570   0.01716  -0.0843   0.9208   0.0483
  -6.250  -0.3149   0.02491   0.01606  -0.0851   0.9162   0.0552
  -6.000  -0.2829   0.02388   0.01506  -0.0865   0.9129   0.0617
  -5.750  -0.2598   0.02326   0.01424  -0.0858   0.9055   0.0677
  -5.500  -0.2306   0.02235   0.01336  -0.0864   0.9011   0.0737
  -5.250  -0.1983   0.02154   0.01243  -0.0874   0.8979   0.0796
  -5.000  -0.1775   0.02096   0.01184  -0.0863   0.8900   0.0853
  -4.750  -0.1482   0.02036   0.01119  -0.0868   0.8856   0.0937
  -4.500  -0.1205   0.01973   0.01056  -0.0870   0.8809   0.1023
  -4.250  -0.0969   0.01927   0.01007  -0.0864   0.8741   0.1139
  -4.000  -0.0676   0.01866   0.00953  -0.0869   0.8699   0.1359
  -3.750  -0.0433   0.01809   0.00914  -0.0867   0.8639   0.1753
  -3.500  -0.0194   0.01730   0.00873  -0.0866   0.8580   0.2653
  -3.250   0.0056   0.01639   0.00864  -0.0864   0.8539   0.4470
  -3.000   0.0274   0.01639   0.00879  -0.0850   0.8469   0.5287
  -2.750   0.0547   0.01642   0.00880  -0.0845   0.8417   0.5730
  -2.500   0.0854   0.01641   0.00872  -0.0846   0.8380   0.6077
  -2.250   0.1059   0.01659   0.00891  -0.0829   0.8301   0.6352
  -2.000   0.1329   0.01667   0.00899  -0.0820   0.8253   0.6658
  -1.750   0.1572   0.01679   0.00907  -0.0808   0.8193   0.6896
  -1.500   0.1817   0.01684   0.00909  -0.0798   0.8127   0.7056
  -1.250   0.2116   0.01678   0.00896  -0.0797   0.8083   0.7204
  -1.000   0.2336   0.01687   0.00900  -0.0785   0.8002   0.7334
  -0.750   0.2627   0.01677   0.00886  -0.0784   0.7949   0.7425
  -0.500   0.2888   0.01677   0.00879  -0.0780   0.7880   0.7503
  -0.250   0.3163   0.01671   0.00868  -0.0778   0.7817   0.7578
   0.000   0.3453   0.01663   0.00855  -0.0779   0.7762   0.7659
   0.250   0.3698   0.01666   0.00856  -0.0772   0.7684   0.7741
   0.500   0.4004   0.01654   0.00839  -0.0775   0.7635   0.7823
   0.750   0.4236   0.01662   0.00848  -0.0766   0.7550   0.7922
   1.000   0.4529   0.01652   0.00836  -0.0766   0.7494   0.8010
   1.250   0.4770   0.01656   0.00841  -0.0759   0.7407   0.8113
   1.500   0.5071   0.01636   0.00818  -0.0759   0.7333   0.8222
   1.750   0.5302   0.01631   0.00817  -0.0748   0.7219   0.8340
   2.000   0.5555   0.01620   0.00809  -0.0740   0.7116   0.8467
   2.250   0.5842   0.01603   0.00792  -0.0737   0.7034   0.8606
   2.500   0.6079   0.01602   0.00799  -0.0728   0.6929   0.8780
   2.750   0.6365   0.01593   0.00797  -0.0728   0.6833   0.8990
   3.000   0.6729   0.01577   0.00784  -0.0742   0.6736   0.9248
   3.250   0.7118   0.01572   0.00784  -0.0765   0.6605   0.9966
   3.500   0.7377   0.01580   0.00790  -0.0763   0.6470   1.0000
   3.750   0.7636   0.01586   0.00793  -0.0760   0.6326   1.0000
   4.000   0.7892   0.01595   0.00799  -0.0756   0.6174   1.0000
   4.250   0.8147   0.01605   0.00807  -0.0752   0.6013   1.0000
   4.500   0.8400   0.01617   0.00815  -0.0746   0.5847   1.0000
   4.750   0.8638   0.01634   0.00829  -0.0739   0.5662   1.0000
   5.000   0.8874   0.01653   0.00847  -0.0731   0.5461   1.0000
   5.250   0.9111   0.01674   0.00861  -0.0723   0.5250   1.0000
   5.500   0.9332   0.01701   0.00883  -0.0713   0.5014   1.0000
   5.750   0.9550   0.01734   0.00906  -0.0702   0.4775   1.0000
   6.000   0.9756   0.01773   0.00937  -0.0690   0.4523   1.0000
   6.250   0.9955   0.01818   0.00973  -0.0677   0.4279   1.0000
   6.500   1.0145   0.01869   0.01013  -0.0663   0.4041   1.0000
   6.750   1.0328   0.01922   0.01063  -0.0649   0.3807   1.0000
   7.000   1.0504   0.01981   0.01113  -0.0634   0.3592   1.0000
   7.250   1.0675   0.02041   0.01169  -0.0618   0.3379   1.0000
   7.500   1.0838   0.02106   0.01227  -0.0602   0.3189   1.0000
   7.750   1.0994   0.02175   0.01289  -0.0585   0.3017   1.0000
   8.000   1.1139   0.02245   0.01356  -0.0566   0.2859   1.0000
   8.500   1.1417   0.02391   0.01499  -0.0529   0.2573   1.0000
   8.750   1.1553   0.02468   0.01577  -0.0510   0.2438   1.0000
   9.000   1.1687   0.02548   0.01660  -0.0493   0.2309   1.0000
   9.250   1.1816   0.02632   0.01749  -0.0475   0.2186   1.0000
   9.500   1.1938   0.02721   0.01840  -0.0458   0.2072   1.0000
   9.750   1.2046   0.02817   0.01937  -0.0439   0.1964   1.0000
  10.000   1.2157   0.02916   0.02041  -0.0423   0.1856   1.0000
  10.250   1.2269   0.03019   0.02151  -0.0407   0.1752   1.0000
  10.500   1.2365   0.03133   0.02268  -0.0390   0.1657   1.0000
  10.750   1.2452   0.03256   0.02397  -0.0374   0.1565   1.0000
  11.000   1.2552   0.03378   0.02529  -0.0360   0.1473   1.0000
  11.250   1.2626   0.03518   0.02672  -0.0345   0.1393   1.0000
  11.500   1.2708   0.03658   0.02824  -0.0332   0.1310   1.0000
  11.750   1.2778   0.03812   0.02986  -0.0319   0.1233   1.0000
  12.000   1.2830   0.03982   0.03162  -0.0306   0.1160   1.0000
  12.250   1.2890   0.04155   0.03346  -0.0295   0.1087   1.0000
  12.500   1.2918   0.04354   0.03550  -0.0284   0.1024   1.0000
  12.750   1.2965   0.04551   0.03763  -0.0274   0.0958   1.0000
  13.000   1.2977   0.04779   0.03997  -0.0266   0.0900   1.0000
  13.250   1.2999   0.05009   0.04239  -0.0260   0.0841   1.0000
  13.500   1.2998   0.05266   0.04506  -0.0255   0.0787   1.0000
  13.750   1.2987   0.05545   0.04792  -0.0252   0.0743   1.0000
  14.000   1.2993   0.05821   0.05085  -0.0251   0.0696   1.0000
  14.250   1.2963   0.06141   0.05414  -0.0252   0.0662   1.0000
  14.500   1.2926   0.06486   0.05768  -0.0255   0.0631   1.0000
  14.750   1.2913   0.06820   0.06122  -0.0259   0.0598   1.0000
  15.000   1.2869   0.07202   0.06520  -0.0266   0.0569   1.0000
  15.250   1.2803   0.07627   0.06955  -0.0277   0.0547   1.0000
  15.500   1.2734   0.08071   0.07406  -0.0290   0.0529   1.0000
  15.750   1.2680   0.08521   0.07881  -0.0305   0.0502   1.0000
  16.000   1.2599   0.09025   0.08403  -0.0324   0.0478   1.0000
  16.250   1.2503   0.09573   0.08968  -0.0348   0.0458   1.0000
  16.500   1.2386   0.10170   0.09575  -0.0376   0.0441   1.0000
  16.750   1.2268   0.10790   0.10207  -0.0406   0.0422   1.0000
  17.000   1.2156   0.11425   0.10864  -0.0438   0.0403   1.0000
  17.250   1.2032   0.12101   0.11556  -0.0474   0.0385   1.0000
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