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HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il)
Reynolds number: 500,000
Max Cl/Cd: 133.24 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1606-il-500000.txt
Download as CSV file: xf-hs1606-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-606 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3465   0.09792   0.09568  -0.0312   1.0000   0.0133
  -8.250  -0.3490   0.09569   0.09350  -0.0309   1.0000   0.0136
  -8.000  -0.3620   0.09468   0.09256  -0.0277   1.0000   0.0137
  -7.750  -0.3487   0.09121   0.08910  -0.0321   0.9966   0.0140
  -7.500  -0.3263   0.08653   0.08441  -0.0391   0.9924   0.0141
  -7.250  -0.3022   0.08161   0.07949  -0.0466   0.9880   0.0142
  -7.000  -0.2820   0.07382   0.07170  -0.0565   0.9845   0.0149
  -6.750  -0.2575   0.07029   0.06815  -0.0614   0.9820   0.0156
  -6.500  -0.2319   0.06662   0.06447  -0.0670   0.9766   0.0165
  -6.250  -0.2004   0.06203   0.05984  -0.0751   0.9725   0.0178
  -6.000  -0.1654   0.05658   0.05434  -0.0847   0.9673   0.0197
  -5.750  -0.1206   0.05097   0.04862  -0.0954   0.9608   0.0218
  -5.500  -0.0852   0.04148   0.03896  -0.1073   0.9556   0.0232
  -5.250  -0.0594   0.03911   0.03652  -0.1097   0.9487   0.0246
  -5.000  -0.0008   0.01777   0.01362  -0.1255   0.9444   0.0119
  -4.750   0.0324   0.01375   0.00870  -0.1267   0.9396   0.0099
  -4.500   0.0617   0.01239   0.00706  -0.1270   0.9345   0.0103
  -4.250   0.0908   0.01150   0.00599  -0.1272   0.9304   0.0111
  -4.000   0.1193   0.01091   0.00527  -0.1273   0.9254   0.0123
  -3.750   0.1478   0.01044   0.00470  -0.1274   0.9206   0.0136
  -3.500   0.1767   0.00985   0.00395  -0.1274   0.9168   0.0138
  -3.250   0.2057   0.00943   0.00341  -0.1275   0.9122   0.0140
  -3.000   0.2345   0.00909   0.00292  -0.1275   0.9080   0.0154
  -2.750   0.2633   0.00858   0.00255  -0.1275   0.9044   0.0598
  -2.500   0.2914   0.00840   0.00248  -0.1276   0.8993   0.0976
  -2.250   0.3191   0.00832   0.00243  -0.1275   0.8938   0.1200
  -2.000   0.3464   0.00829   0.00242  -0.1273   0.8876   0.1422
  -1.750   0.3736   0.00827   0.00238  -0.1270   0.8803   0.1596
  -1.500   0.4011   0.00824   0.00232  -0.1268   0.8742   0.1715
  -1.250   0.4290   0.00820   0.00229  -0.1267   0.8681   0.1829
  -1.000   0.4567   0.00819   0.00224  -0.1265   0.8629   0.1936
  -0.750   0.4845   0.00816   0.00221  -0.1264   0.8565   0.2032
  -0.500   0.5123   0.00810   0.00216  -0.1263   0.8506   0.2124
  -0.250   0.5403   0.00808   0.00215  -0.1263   0.8454   0.2228
   0.000   0.5684   0.00806   0.00214  -0.1263   0.8402   0.2336
   0.250   0.5964   0.00802   0.00213  -0.1263   0.8354   0.2459
   0.500   0.6245   0.00797   0.00214  -0.1263   0.8296   0.2605
   0.750   0.6525   0.00789   0.00215  -0.1263   0.8237   0.2794
   1.000   0.6806   0.00776   0.00218  -0.1264   0.8180   0.3250
   1.250   0.7015   0.00634   0.00227  -0.1249   0.8112   1.0000
   1.500   0.7293   0.00640   0.00227  -0.1248   0.8042   1.0000
   1.750   0.7569   0.00644   0.00229  -0.1246   0.7957   1.0000
   2.000   0.7846   0.00648   0.00232  -0.1244   0.7870   1.0000
   2.250   0.8121   0.00654   0.00235  -0.1242   0.7782   1.0000
   2.500   0.8390   0.00657   0.00239  -0.1239   0.7630   1.0000
   2.750   0.8652   0.00661   0.00237  -0.1233   0.7377   1.0000
   3.000   0.8914   0.00669   0.00240  -0.1228   0.7096   1.0000
   3.250   0.9157   0.00693   0.00242  -0.1218   0.6476   1.0000
   3.500   0.9357   0.00769   0.00268  -0.1202   0.5456   1.0000
   3.750   0.9572   0.00844   0.00304  -0.1192   0.4642   1.0000
   4.000   0.9791   0.00918   0.00342  -0.1182   0.3893   1.0000
   4.250   1.0020   0.00980   0.00379  -0.1175   0.3359   1.0000
   4.500   1.0247   0.01045   0.00417  -0.1167   0.2790   1.0000
   4.750   1.0444   0.01149   0.00471  -0.1156   0.1799   1.0000
   5.000   1.0599   0.01312   0.00565  -0.1138   0.0617   1.0000
   5.250   1.0829   0.01378   0.00628  -0.1130   0.0484   1.0000
   5.500   1.1059   0.01442   0.00692  -0.1121   0.0418   1.0000
   5.750   1.1284   0.01511   0.00768  -0.1111   0.0378   1.0000
   6.000   1.1519   0.01561   0.00827  -0.1104   0.0352   1.0000
   6.250   1.1744   0.01624   0.00896  -0.1095   0.0326   1.0000
   6.500   1.1949   0.01709   0.00986  -0.1082   0.0302   1.0000
   6.750   1.2091   0.01881   0.01171  -0.1058   0.0280   1.0000
   7.000   1.2294   0.01973   0.01272  -0.1045   0.0274   1.0000
   7.250   1.2513   0.02039   0.01346  -0.1035   0.0264   1.0000
   7.500   1.2725   0.02115   0.01432  -0.1024   0.0250   1.0000
   7.750   1.2933   0.02193   0.01522  -0.1012   0.0234   1.0000
   8.000   1.3153   0.02226   0.01557  -0.1005   0.0213   1.0000
   8.250   1.3279   0.02479   0.01822  -0.0983   0.0186   1.0000
   8.500   1.3516   0.02433   0.01782  -0.0978   0.0175   1.0000
   8.750   1.3744   0.02427   0.01784  -0.0971   0.0157   1.0000
   9.000   1.3973   0.02421   0.01779  -0.0966   0.0137   1.0000
   9.250   1.4119   0.02536   0.01901  -0.0947   0.0111   1.0000
   9.500   1.4380   0.02495   0.01859  -0.0946   0.0084   1.0000
   9.750   1.4463   0.02671   0.02047  -0.0916   0.0067   1.0000
  10.000   1.4580   0.02795   0.02190  -0.0891   0.0059   1.0000
  10.250   1.4661   0.02932   0.02343  -0.0861   0.0054   1.0000
  10.500   1.4736   0.03074   0.02499  -0.0832   0.0051   1.0000
  10.750   1.4799   0.03225   0.02666  -0.0803   0.0048   1.0000
  11.000   1.4832   0.03409   0.02866  -0.0772   0.0045   1.0000
  11.250   1.4795   0.03682   0.03164  -0.0736   0.0043   1.0000
  11.500   1.4657   0.04091   0.03610  -0.0693   0.0041   1.0000
  11.750   1.4628   0.04357   0.03900  -0.0666   0.0040   1.0000
  12.000   1.4631   0.04583   0.04146  -0.0645   0.0039   1.0000
  12.250   1.4596   0.04861   0.04446  -0.0625   0.0037   1.0000
  12.500   1.4517   0.05204   0.04812  -0.0607   0.0036   1.0000
  12.750   1.4406   0.05601   0.05232  -0.0592   0.0036   1.0000
  13.000   1.4262   0.06064   0.05719  -0.0584   0.0035   1.0000
  13.250   1.4098   0.06583   0.06261  -0.0583   0.0035   1.0000
  13.500   1.3895   0.07206   0.06908  -0.0593   0.0035   1.0000
  13.750   1.3665   0.07943   0.07668  -0.0617   0.0035   1.0000
  14.000   1.3434   0.08771   0.08517  -0.0655   0.0036   1.0000
  14.250   1.3194   0.09726   0.09493  -0.0708   0.0036   1.0000
  14.500   1.2942   0.10806   0.10591  -0.0773   0.0037   1.0000
  14.750   1.2471   0.12534   0.12338  -0.0877   0.0040   1.0000
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