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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 50,000
Max Cl/Cd: 40.94 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq358-il-50000.txt
Download as CSV file: xf-hq358-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/8 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3764   0.09932   0.09308  -0.0271   1.0000   0.1763
  -7.250  -0.3702   0.09578   0.08960  -0.0253   1.0000   0.1839
  -7.000  -0.3880   0.09508   0.08908  -0.0240   1.0000   0.1899
  -6.750  -0.3835   0.09180   0.08587  -0.0217   1.0000   0.1988
  -6.500  -0.4043   0.09128   0.08552  -0.0233   1.0000   0.2047
  -6.250  -0.4004   0.08813   0.08243  -0.0202   1.0000   0.2172
  -6.000  -0.4005   0.08544   0.07982  -0.0180   1.0000   0.2295
  -5.750  -0.4032   0.08304   0.07751  -0.0164   1.0000   0.2430
  -5.500  -0.4096   0.08103   0.07559  -0.0166   1.0000   0.2589
  -5.250  -0.4062   0.07812   0.07276  -0.0122   1.0000   0.2784
  -5.000  -0.4099   0.07602   0.07074  -0.0109   1.0000   0.3028
  -4.750  -0.4067   0.07376   0.06855  -0.0049   1.0000   0.3349
  -4.500  -0.4067   0.07184   0.06672   0.0009   1.0000   0.3768
  -4.250  -0.4082   0.07010   0.06507   0.0075   1.0000   0.4267
  -3.000  -0.2122   0.04176   0.03468  -0.0556   1.0000   0.2179
  -2.750  -0.1577   0.03703   0.02889  -0.0607   1.0000   0.1435
  -2.500  -0.1189   0.03434   0.02536  -0.0622   1.0000   0.1201
  -2.250  -0.0848   0.03237   0.02260  -0.0627   1.0000   0.1088
  -2.000  -0.0561   0.03021   0.02017  -0.0627   1.0000   0.1061
  -1.750  -0.0280   0.02867   0.01824  -0.0624   1.0000   0.1066
  -1.500  -0.0029   0.02729   0.01672  -0.0618   1.0000   0.1168
  -1.250   0.0220   0.02612   0.01537  -0.0607   1.0000   0.1264
  -1.000   0.0488   0.02502   0.01418  -0.0600   1.0000   0.1444
  -0.750   0.0882   0.02125   0.01302  -0.0616   1.0000   0.6537
  -0.500   0.0926   0.02046   0.01215  -0.0554   1.0000   1.0000
  -0.250   0.1161   0.02091   0.01201  -0.0553   1.0000   1.0000
   0.000   0.1389   0.02139   0.01208  -0.0553   1.0000   1.0000
   0.250   0.1611   0.02191   0.01226  -0.0553   1.0000   1.0000
   0.500   0.1829   0.02247   0.01255  -0.0553   1.0000   1.0000
   0.750   0.2041   0.02307   0.01288  -0.0554   1.0000   1.0000
   1.000   0.2248   0.02372   0.01333  -0.0554   1.0000   1.0000
   1.250   0.2452   0.02441   0.01387  -0.0554   1.0000   1.0000
   1.500   0.2651   0.02516   0.01448  -0.0554   1.0000   1.0000
   1.750   0.2844   0.02597   0.01518  -0.0555   1.0000   1.0000
   2.000   0.3033   0.02683   0.01597  -0.0556   1.0000   1.0000
   2.250   0.3216   0.02777   0.01682  -0.0557   1.0000   1.0000
   2.500   0.3777   0.02952   0.01851  -0.0628   0.9812   1.0000
   2.750   0.4403   0.03100   0.02000  -0.0705   0.9555   1.0000
   3.000   0.4922   0.03200   0.02107  -0.0758   0.9305   1.0000
   3.250   0.5379   0.03283   0.02197  -0.0796   0.9074   1.0000
   3.500   0.5864   0.03350   0.02276  -0.0836   0.8848   1.0000
   3.750   0.6385   0.03389   0.02331  -0.0876   0.8622   1.0000
   4.000   0.6818   0.03408   0.02378  -0.0898   0.8373   1.0000
   4.250   0.7284   0.03396   0.02389  -0.0920   0.8117   1.0000
   4.500   0.7790   0.03336   0.02358  -0.0940   0.7855   1.0000
   4.750   0.8347   0.03210   0.02277  -0.0959   0.7585   1.0000
   5.000   0.8894   0.03032   0.02136  -0.0966   0.7299   1.0000
   5.250   0.9370   0.02859   0.01995  -0.0960   0.6962   1.0000
   5.500   0.9828   0.02690   0.01850  -0.0948   0.6576   1.0000
   5.750   1.0170   0.02615   0.01796  -0.0929   0.6135   1.0000
   6.000   1.0476   0.02594   0.01776  -0.0910   0.5696   1.0000
   6.250   1.0747   0.02625   0.01804  -0.0891   0.5276   1.0000
   6.500   1.0990   0.02694   0.01870  -0.0873   0.4871   1.0000
   6.750   1.1213   0.02786   0.01959  -0.0853   0.4468   1.0000
   7.000   1.1418   0.02896   0.02064  -0.0832   0.4053   1.0000
   7.250   1.1595   0.03017   0.02190  -0.0807   0.3601   1.0000
   7.500   1.1684   0.03122   0.02278  -0.0770   0.3058   1.0000
   7.750   1.1676   0.03261   0.02379  -0.0724   0.2395   1.0000
   8.000   1.1577   0.03473   0.02553  -0.0667   0.1668   1.0000
   8.250   1.1557   0.03744   0.02772  -0.0627   0.1151   1.0000
   8.500   1.1713   0.04077   0.03085  -0.0608   0.0871   1.0000
   8.750   1.1925   0.04411   0.03419  -0.0597   0.0726   1.0000
   9.000   1.2192   0.04859   0.03906  -0.0589   0.0671   1.0000
   9.250   1.2357   0.05291   0.04395  -0.0571   0.0647   1.0000
   9.500   1.2448   0.05738   0.04895  -0.0550   0.0637   1.0000
   9.750   1.2461   0.06197   0.05406  -0.0526   0.0636   1.0000
  10.000   1.2403   0.06658   0.05915  -0.0500   0.0641   1.0000
  10.250   1.2287   0.07112   0.06409  -0.0474   0.0647   1.0000
  10.500   1.2119   0.07531   0.06860  -0.0447   0.0654   1.0000
  10.750   1.1924   0.07963   0.07316  -0.0428   0.0661   1.0000
  11.000   1.1715   0.08434   0.07809  -0.0420   0.0668   1.0000
  11.250   1.1497   0.08958   0.08351  -0.0424   0.0674   1.0000
  11.500   1.1285   0.09541   0.08947  -0.0440   0.0682   1.0000
  11.750   1.1095   0.10179   0.09595  -0.0466   0.0689   1.0000
  12.000   1.0942   0.10859   0.10281  -0.0496   0.0697   1.0000
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