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HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il)
Reynolds number: 50,000
Max Cl/Cd: 42.53 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1404-il-50000-n5.txt
Download as CSV file: xf-hs1404-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-404 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3770   0.10572   0.09914  -0.0176   1.0000   0.0810
  -8.500  -0.3812   0.10369   0.09720  -0.0195   1.0000   0.0815
  -8.250  -0.3851   0.10152   0.09511  -0.0214   1.0000   0.0818
  -8.000  -0.3666   0.09440   0.08799  -0.0190   1.0000   0.0838
  -7.750  -0.3616   0.09063   0.08427  -0.0190   1.0000   0.0855
  -7.500  -0.3592   0.08726   0.08082  -0.0193   1.0000   0.0870
  -7.250  -0.3585   0.08407   0.07771  -0.0196   1.0000   0.0887
  -7.000  -0.3588   0.08102   0.07474  -0.0203   1.0000   0.0905
  -6.750  -0.3607   0.07849   0.07231  -0.0241   1.0000   0.0939
  -6.500  -0.3582   0.07554   0.06941  -0.0289   1.0000   0.0947
  -6.250  -0.3517   0.07172   0.06562  -0.0319   1.0000   0.0949
  -6.000  -0.3442   0.06650   0.06047  -0.0261   1.0000   0.0886
  -5.750  -0.3339   0.06032   0.05422  -0.0303   1.0000   0.0480
  -5.500  -0.3433   0.06752   0.06071  -0.0409   1.0000   0.0412
  -5.250  -0.3276   0.06353   0.05672  -0.0426   1.0000   0.0390
  -5.000  -0.3063   0.05918   0.05229  -0.0461   1.0000   0.0369
  -4.750  -0.2807   0.05446   0.04745  -0.0504   1.0000   0.0349
  -4.500  -0.2502   0.04926   0.04201  -0.0553   1.0000   0.0330
  -4.000  -0.1819   0.03923   0.03106  -0.0634   1.0000   0.0302
  -3.750  -0.1521   0.03525   0.02664  -0.0657   1.0000   0.0299
  -3.500  -0.1212   0.03160   0.02244  -0.0675   1.0000   0.0299
  -3.250  -0.0905   0.02844   0.01866  -0.0686   1.0000   0.0300
  -3.000  -0.0621   0.02596   0.01581  -0.0694   1.0000   0.0331
  -2.750  -0.0345   0.02426   0.01369  -0.0694   1.0000   0.0396
  -2.500  -0.0062   0.02247   0.01145  -0.0693   1.0000   0.0449
  -2.250   0.0222   0.02103   0.00966  -0.0689   1.0000   0.0526
  -2.000   0.0521   0.01974   0.00829  -0.0691   1.0000   0.0989
  -1.750   0.0793   0.01925   0.00801  -0.0692   1.0000   0.2166
  -1.500   0.1059   0.01864   0.00729  -0.0691   1.0000   0.2694
  -1.250   0.1327   0.01802   0.00670  -0.0691   1.0000   0.3215
  -1.000   0.1603   0.01702   0.00629  -0.0696   1.0000   0.4439
  -0.750   0.1718   0.01580   0.00598  -0.0658   1.0000   1.0000
  -0.500   0.1971   0.01601   0.00578  -0.0655   1.0000   1.0000
  -0.250   0.2220   0.01624   0.00558  -0.0652   1.0000   1.0000
   0.000   0.2465   0.01649   0.00559  -0.0650   1.0000   1.0000
   0.250   0.2708   0.01677   0.00568  -0.0647   1.0000   1.0000
   0.500   0.2949   0.01707   0.00584  -0.0645   1.0000   1.0000
   0.750   0.3187   0.01740   0.00607  -0.0642   1.0000   1.0000
   1.000   0.3424   0.01775   0.00637  -0.0640   1.0000   1.0000
   1.250   0.3658   0.01814   0.00674  -0.0639   1.0000   1.0000
   1.500   0.3891   0.01856   0.00720  -0.0637   1.0000   1.0000
   1.750   0.4214   0.01900   0.00768  -0.0654   0.9950   1.0000
   2.000   0.4680   0.01939   0.00818  -0.0697   0.9808   1.0000
   2.250   0.5130   0.01968   0.00864  -0.0735   0.9641   1.0000
   2.500   0.5556   0.01993   0.00911  -0.0766   0.9484   1.0000
   2.750   0.5967   0.02015   0.00978  -0.0793   0.9333   1.0000
   3.000   0.6396   0.02029   0.01027  -0.0821   0.9180   1.0000
   3.250   0.6778   0.02038   0.01073  -0.0837   0.8992   1.0000
   3.500   0.7179   0.02030   0.01111  -0.0851   0.8781   1.0000
   3.750   0.7567   0.01917   0.01037  -0.0830   0.8118   1.0000
   4.000   0.7788   0.01831   0.00930  -0.0769   0.6345   1.0000
   4.250   0.7904   0.02010   0.00957  -0.0715   0.3385   1.0000
   4.500   0.8020   0.02328   0.01121  -0.0697   0.1260   1.0000
   4.750   0.8230   0.02535   0.01316  -0.0684   0.0943   1.0000
   5.000   0.8447   0.02719   0.01498  -0.0675   0.0712   1.0000
   5.250   0.8683   0.02914   0.01717  -0.0661   0.0614   1.0000
   5.500   0.8954   0.03163   0.01994  -0.0648   0.0555   1.0000
   5.750   0.9212   0.03448   0.02293  -0.0639   0.0475   1.0000
   6.000   0.9461   0.03708   0.02609  -0.0627   0.0389   1.0000
   6.250   0.9689   0.04080   0.03014  -0.0616   0.0356   1.0000
   6.500   0.9886   0.04541   0.03526  -0.0601   0.0340   1.0000
   6.750   1.0057   0.04952   0.04015  -0.0581   0.0327   1.0000
   7.000   1.0184   0.05366   0.04502  -0.0562   0.0300   1.0000
   7.250   1.0275   0.05750   0.04956  -0.0547   0.0263   1.0000
   7.500   1.0345   0.06127   0.05357  -0.0536   0.0241   1.0000
   7.750   1.0371   0.06602   0.05870  -0.0521   0.0238   1.0000
   8.000   1.0362   0.07082   0.06386  -0.0509   0.0237   1.0000
   8.250   1.0318   0.07563   0.06899  -0.0499   0.0239   1.0000
   8.500   1.0218   0.08063   0.07429  -0.0494   0.0242   1.0000
   8.750   1.0073   0.08559   0.07946  -0.0493   0.0247   1.0000
   9.000   0.9909   0.09088   0.08487  -0.0506   0.0253   1.0000
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