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HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il)
Reynolds number: 50,000
Max Cl/Cd: 32.5 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3013-il-50000.txt
Download as CSV file: xf-hq3013-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3557   0.13004   0.12292  -0.0349   1.0000   0.2230
 -10.750  -0.3297   0.12421   0.11707  -0.0335   1.0000   0.2319
 -10.500  -0.3581   0.12490   0.11793  -0.0350   1.0000   0.2386
 -10.250  -0.3282   0.11887   0.11187  -0.0332   1.0000   0.2502
 -10.000  -0.3241   0.11568   0.10874  -0.0326   1.0000   0.2597
  -9.750  -0.3449   0.11544   0.10865  -0.0328   1.0000   0.2689
  -9.500  -0.3334   0.11180   0.10505  -0.0313   1.0000   0.2834
  -9.250  -0.3263   0.10863   0.10193  -0.0298   1.0000   0.2979
  -9.000  -0.3180   0.10528   0.09863  -0.0285   1.0000   0.3094
  -8.750  -0.3210   0.10291   0.09636  -0.0271   1.0000   0.3204
  -8.500  -0.3290   0.10113   0.09470  -0.0252   1.0000   0.3335
  -8.250  -0.3241   0.09853   0.09215  -0.0229   1.0000   0.3504
  -8.000  -0.3221   0.09632   0.09001  -0.0203   1.0000   0.3680
  -7.750  -0.3266   0.09449   0.08828  -0.0174   1.0000   0.3822
  -7.500  -0.3352   0.09292   0.08681  -0.0143   1.0000   0.3955
  -7.250  -0.3424   0.09133   0.08530  -0.0109   1.0000   0.4101
  -7.000  -0.3418   0.08933   0.08336  -0.0077   1.0000   0.4285
  -6.750  -0.3494   0.08772   0.08184  -0.0043   1.0000   0.4426
  -6.500  -0.3630   0.08643   0.08065  -0.0006   1.0000   0.4551
  -6.250  -0.5624   0.06095   0.05450  -0.0391   1.0000   0.1484
  -6.000  -0.5526   0.05685   0.05023  -0.0388   1.0000   0.1455
  -5.750  -0.5417   0.05237   0.04542  -0.0393   1.0000   0.1420
  -5.500  -0.5271   0.04795   0.04048  -0.0402   1.0000   0.1400
  -5.250  -0.5092   0.04445   0.03643  -0.0407   1.0000   0.1433
  -5.000  -0.4879   0.04119   0.03244  -0.0411   1.0000   0.1462
  -4.750  -0.4682   0.03883   0.02995  -0.0407   1.0000   0.1539
  -4.500  -0.4451   0.03664   0.02721  -0.0406   1.0000   0.1607
  -4.250  -0.4238   0.03484   0.02528  -0.0401   1.0000   0.1700
  -4.000  -0.4002   0.03325   0.02320  -0.0396   1.0000   0.1787
  -3.750  -0.3789   0.03202   0.02190  -0.0389   1.0000   0.1910
  -3.500  -0.3572   0.03081   0.02068  -0.0380   1.0000   0.2023
  -3.250  -0.3359   0.02988   0.01971  -0.0371   1.0000   0.2197
  -3.000  -0.3147   0.02895   0.01887  -0.0361   1.0000   0.2420
  -2.750  -0.2935   0.02797   0.01807  -0.0352   1.0000   0.2782
  -2.500  -0.2709   0.02609   0.01762  -0.0347   1.0000   0.4164
  -2.250  -0.2763   0.02653   0.01919  -0.0247   1.0000   0.6851
  -2.000  -0.2780   0.02704   0.01973  -0.0169   1.0000   0.7597
  -1.750  -0.2781   0.02717   0.01985  -0.0100   1.0000   0.8122
  -1.500  -0.2756   0.02707   0.01971  -0.0040   1.0000   0.8630
  -1.250  -0.2546   0.02708   0.01969  -0.0014   1.0000   0.9284
  -1.000  -0.1681   0.02823   0.02041  -0.0133   1.0000   1.0000
  -0.750  -0.1679   0.02773   0.01977  -0.0117   1.0000   1.0000
  -0.500  -0.1555   0.02765   0.01949  -0.0120   1.0000   1.0000
  -0.250  -0.1363   0.02789   0.01950  -0.0132   1.0000   1.0000
   0.000  -0.1144   0.02833   0.01972  -0.0148   1.0000   1.0000
   0.250  -0.0693   0.02969   0.02079  -0.0206   0.9898   1.0000
   0.500  -0.0226   0.03114   0.02198  -0.0263   0.9769   1.0000
   0.750   0.0206   0.03247   0.02309  -0.0313   0.9639   1.0000
   1.000   0.0618   0.03377   0.02418  -0.0356   0.9509   1.0000
   1.250   0.1021   0.03505   0.02529  -0.0396   0.9376   1.0000
   1.500   0.1419   0.03631   0.02640  -0.0434   0.9241   1.0000
   1.750   0.1803   0.03751   0.02747  -0.0468   0.9097   1.0000
   2.000   0.2172   0.03863   0.02848  -0.0497   0.8947   1.0000
   2.250   0.2514   0.03967   0.02944  -0.0520   0.8788   1.0000
   2.500   0.2843   0.04065   0.03036  -0.0540   0.8623   1.0000
   2.750   0.3169   0.04162   0.03128  -0.0557   0.8454   1.0000
   3.000   0.3497   0.04257   0.03219  -0.0574   0.8285   1.0000
   3.250   0.3828   0.04349   0.03309  -0.0590   0.8116   1.0000
   3.500   0.4162   0.04438   0.03398  -0.0605   0.7950   1.0000
   3.750   0.4507   0.04520   0.03481  -0.0620   0.7784   1.0000
   4.000   0.4870   0.04591   0.03554  -0.0634   0.7617   1.0000
   4.250   0.5248   0.04649   0.03617  -0.0648   0.7451   1.0000
   4.500   0.5520   0.04717   0.03689  -0.0649   0.7270   1.0000
   4.750   0.5761   0.04788   0.03765  -0.0647   0.7080   1.0000
   5.000   0.6097   0.04820   0.03806  -0.0650   0.6897   1.0000
   5.250   0.6500   0.04807   0.03802  -0.0657   0.6722   1.0000
   5.500   0.6938   0.04755   0.03762  -0.0663   0.6555   1.0000
   5.750   0.7192   0.04781   0.03798  -0.0654   0.6360   1.0000
   6.000   0.7471   0.04788   0.03815  -0.0646   0.6169   1.0000
   6.250   0.7887   0.04682   0.03726  -0.0642   0.5998   1.0000
   6.500   0.8381   0.04489   0.03549  -0.0639   0.5840   1.0000
   6.750   0.9028   0.04183   0.03267  -0.0646   0.5679   1.0000
   7.000   0.9815   0.03785   0.02886  -0.0665   0.5502   1.0000
   7.250   1.0043   0.03786   0.02899  -0.0647   0.5273   1.0000
   7.500   1.0675   0.03535   0.02649  -0.0660   0.5035   1.0000
   7.750   1.0926   0.03555   0.02672  -0.0646   0.4792   1.0000
   8.000   1.1246   0.03555   0.02673  -0.0639   0.4552   1.0000
   8.250   1.1591   0.03566   0.02674  -0.0636   0.4311   1.0000
   8.500   1.1764   0.03680   0.02793  -0.0619   0.4096   1.0000
   8.750   1.2006   0.03769   0.02880  -0.0609   0.3882   1.0000
   9.000   1.2254   0.03868   0.02977  -0.0600   0.3676   1.0000
   9.250   1.2387   0.04020   0.03140  -0.0580   0.3493   1.0000
   9.500   1.2555   0.04157   0.03282  -0.0564   0.3310   1.0000
   9.750   1.2787   0.04275   0.03395  -0.0555   0.3122   1.0000
  10.000   1.3001   0.04420   0.03534  -0.0544   0.2943   1.0000
  10.250   1.3113   0.04604   0.03732  -0.0524   0.2786   1.0000
  10.500   1.3222   0.04795   0.03933  -0.0504   0.2634   1.0000
  10.750   1.3338   0.04995   0.04142  -0.0485   0.2488   1.0000
  11.000   1.3460   0.05194   0.04346  -0.0468   0.2348   1.0000
  11.250   1.3280   0.05512   0.04707  -0.0424   0.2277   1.0000
  11.500   1.3330   0.05760   0.04965  -0.0403   0.2171   1.0000
  11.750   1.3474   0.05967   0.05172  -0.0390   0.2050   1.0000
  12.000   1.3149   0.06346   0.05587  -0.0341   0.2029   1.0000
  12.250   1.2795   0.06799   0.06066  -0.0304   0.2017   1.0000
  12.500   1.2356   0.07401   0.06691  -0.0282   0.2022   1.0000
  12.750   1.1842   0.08215   0.07520  -0.0283   0.2041   1.0000
  13.000   1.1311   0.09264   0.08574  -0.0310   0.2061   1.0000
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