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HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il)
Reynolds number: 200,000
Max Cl/Cd: 84.54 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1404-il-200000.txt
Download as CSV file: xf-hs1404-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4796   0.12046   0.11680  -0.0065   1.0000   0.0183
  -9.000  -0.4733   0.11709   0.11345  -0.0082   1.0000   0.0183
  -8.750  -0.4718   0.10972   0.10613  -0.0073   1.0000   0.0193
  -8.500  -0.4639   0.10572   0.10214  -0.0068   1.0000   0.0202
  -8.250  -0.4575   0.10242   0.09887  -0.0076   1.0000   0.0209
  -8.000  -0.4515   0.09924   0.09571  -0.0087   1.0000   0.0216
  -7.750  -0.4459   0.09612   0.09262  -0.0100   1.0000   0.0224
  -7.500  -0.4408   0.09306   0.08960  -0.0113   1.0000   0.0231
  -7.250  -0.4356   0.09000   0.08658  -0.0129   1.0000   0.0239
  -7.000  -0.4270   0.08663   0.08325  -0.0156   1.0000   0.0249
  -6.750  -0.4169   0.08315   0.07979  -0.0189   1.0000   0.0260
  -6.500  -0.4048   0.07956   0.07616  -0.0227   1.0000   0.0273
  -6.250  -0.3876   0.07595   0.07256  -0.0287   1.0000   0.0288
  -6.000  -0.3613   0.07234   0.06892  -0.0373   1.0000   0.0299
  -5.750  -0.3396   0.06858   0.06512  -0.0422   1.0000   0.0301
  -5.500  -0.3189   0.06459   0.06106  -0.0460   1.0000   0.0303
  -5.250  -0.3202   0.05876   0.05532  -0.0452   1.0000   0.0318
  -5.000  -0.3101   0.05600   0.05258  -0.0445   1.0000   0.0335
  -4.750  -0.2930   0.05279   0.04932  -0.0462   1.0000   0.0358
  -4.500  -0.2687   0.04897   0.04540  -0.0496   1.0000   0.0393
  -4.250  -0.2231   0.04300   0.03897  -0.0578   1.0000   0.0435
  -4.000  -0.2112   0.03976   0.03581  -0.0573   1.0000   0.0455
  -3.750  -0.1906   0.03741   0.03338  -0.0578   1.0000   0.0513
  -2.750  -0.0456   0.02009   0.01380  -0.0663   1.0000   0.0305
  -2.500  -0.0076   0.01662   0.00980  -0.0683   1.0000   0.0271
  -2.250   0.0275   0.01481   0.00764  -0.0693   1.0000   0.0254
  -2.000   0.0606   0.01359   0.00618  -0.0701   1.0000   0.0252
  -1.750   0.0923   0.01279   0.00525  -0.0708   1.0000   0.0266
  -1.500   0.1241   0.01216   0.00449  -0.0714   1.0000   0.0368
  -1.250   0.1544   0.01166   0.00468  -0.0725   1.0000   0.2303
  -1.000   0.1807   0.01162   0.00470  -0.0727   1.0000   0.2725
  -0.750   0.2132   0.01139   0.00462  -0.0742   0.9986   0.3210
  -0.500   0.2437   0.00961   0.00447  -0.0747   0.9964   1.0000
  -0.250   0.2825   0.00974   0.00440  -0.0772   0.9918   1.0000
   0.000   0.3239   0.00982   0.00434  -0.0802   0.9856   1.0000
   0.250   0.3675   0.00982   0.00425  -0.0836   0.9777   1.0000
   0.500   0.4130   0.00975   0.00415  -0.0873   0.9707   1.0000
   0.750   0.4494   0.00976   0.00417  -0.0891   0.9629   1.0000
   1.000   0.4905   0.00972   0.00414  -0.0920   0.9581   1.0000
   1.250   0.5257   0.00972   0.00417  -0.0935   0.9507   1.0000
   1.500   0.5640   0.00963   0.00414  -0.0955   0.9444   1.0000
   1.750   0.5960   0.00959   0.00418  -0.0961   0.9347   1.0000
   2.000   0.6280   0.00950   0.00418  -0.0965   0.9246   1.0000
   2.250   0.6572   0.00925   0.00410  -0.0956   0.9074   1.0000
   2.500   0.6805   0.00895   0.00382  -0.0931   0.8797   1.0000
   2.750   0.7019   0.00880   0.00367  -0.0903   0.8456   1.0000
   3.000   0.7240   0.00876   0.00360  -0.0880   0.8040   1.0000
   3.250   0.7465   0.00883   0.00361  -0.0859   0.7487   1.0000
   3.500   0.7659   0.00926   0.00356  -0.0831   0.6084   1.0000
   3.750   0.7757   0.01156   0.00420  -0.0799   0.3015   1.0000
   4.000   0.7896   0.01444   0.00581  -0.0782   0.0724   1.0000
   4.250   0.8123   0.01568   0.00711  -0.0771   0.0572   1.0000
   4.500   0.8343   0.01715   0.00859  -0.0759   0.0484   1.0000
   4.750   0.8582   0.01834   0.00991  -0.0749   0.0408   1.0000
   5.000   0.8804   0.02150   0.01307  -0.0736   0.0344   1.0000
   5.250   0.9050   0.02247   0.01423  -0.0727   0.0238   1.0000
   5.500   0.9302   0.02444   0.01657  -0.0714   0.0172   1.0000
   5.750   0.9509   0.02716   0.01955  -0.0704   0.0124   1.0000
   6.000   0.9691   0.03286   0.02594  -0.0682   0.0119   1.0000
   6.250   0.9868   0.03700   0.03059  -0.0662   0.0120   1.0000
   6.500   1.0067   0.03968   0.03362  -0.0645   0.0124   1.0000
   6.750   1.0234   0.04665   0.04149  -0.0604   0.0175   1.0000
   7.000   1.0327   0.05405   0.04947  -0.0574   0.0274   1.0000
   7.250   1.0389   0.05889   0.05464  -0.0557   0.0272   1.0000
   7.500   1.0423   0.06360   0.05962  -0.0543   0.0266   1.0000
   7.750   1.0427   0.06827   0.06452  -0.0532   0.0261   1.0000
   8.000   1.0399   0.07292   0.06936  -0.0522   0.0256   1.0000
   8.250   1.0339   0.07755   0.07425  -0.0516   0.0253   1.0000
   8.500   1.0237   0.08213   0.07895  -0.0512   0.0251   1.0000
   8.750   1.0079   0.08673   0.08357  -0.0513   0.0251   1.0000
   9.000   0.9918   0.09257   0.08951  -0.0543   0.0252   1.0000
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