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HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il)
Reynolds number: 100,000
Max Cl/Cd: 66.26 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1606-il-100000-n5.txt
Download as CSV file: xf-hs1606-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3660   0.09450   0.08981  -0.0272   1.0000   0.0292
  -7.250  -0.3736   0.09266   0.08806  -0.0251   1.0000   0.0284
  -7.000  -0.3810   0.09076   0.08625  -0.0236   1.0000   0.0278
  -6.000  -0.3039   0.07018   0.06558  -0.0516   0.9840   0.0219
  -5.750  -0.2811   0.06544   0.06080  -0.0566   0.9791   0.0212
  -5.500  -0.2507   0.06007   0.05533  -0.0639   0.9745   0.0207
  -5.250  -0.2127   0.05390   0.04902  -0.0729   0.9713   0.0202
  -5.000  -0.1719   0.04713   0.04203  -0.0821   0.9677   0.0198
  -4.750  -0.1252   0.03837   0.03283  -0.0923   0.9644   0.0192
  -4.500  -0.0717   0.02811   0.02140  -0.1026   0.9633   0.0188
  -4.250  -0.0322   0.02422   0.01666  -0.1062   0.9616   0.0192
  -4.000   0.0042   0.02205   0.01393  -0.1084   0.9598   0.0201
  -3.750   0.0405   0.02059   0.01202  -0.1102   0.9581   0.0215
  -3.500   0.0772   0.01937   0.01052  -0.1123   0.9566   0.0254
  -3.250   0.1077   0.01851   0.00959  -0.1130   0.9527   0.0410
  -3.000   0.1384   0.01849   0.00973  -0.1139   0.9489   0.0995
  -2.750   0.1714   0.01859   0.00961  -0.1151   0.9459   0.1228
  -2.500   0.2062   0.01827   0.00912  -0.1166   0.9438   0.1347
  -2.250   0.2359   0.01810   0.00887  -0.1171   0.9399   0.1474
  -2.000   0.2657   0.01798   0.00866  -0.1176   0.9358   0.1624
  -1.750   0.2987   0.01779   0.00839  -0.1188   0.9329   0.1772
  -1.500   0.3331   0.01763   0.00820  -0.1202   0.9304   0.1942
  -1.250   0.3612   0.01754   0.00809  -0.1204   0.9250   0.2092
  -1.000   0.3934   0.01737   0.00791  -0.1213   0.9203   0.2260
  -0.750   0.4288   0.01713   0.00767  -0.1228   0.9170   0.2445
  -0.500   0.4557   0.01707   0.00761  -0.1226   0.9105   0.2607
  -0.250   0.4885   0.01688   0.00747  -0.1237   0.9064   0.2799
   0.000   0.5223   0.01667   0.00734  -0.1248   0.9027   0.3039
   0.250   0.5502   0.01649   0.00733  -0.1248   0.8949   0.3408
   0.750   0.6079   0.01475   0.00688  -0.1239   0.8781   1.0000
   1.000   0.6363   0.01472   0.00677  -0.1235   0.8678   1.0000
   1.250   0.6675   0.01467   0.00667  -0.1238   0.8607   1.0000
   1.500   0.6944   0.01476   0.00677  -0.1234   0.8520   1.0000
   1.750   0.7225   0.01481   0.00683  -0.1231   0.8440   1.0000
   2.000   0.7516   0.01481   0.00684  -0.1230   0.8359   1.0000
   2.250   0.7777   0.01489   0.00697  -0.1224   0.8255   1.0000
   2.500   0.8050   0.01492   0.00704  -0.1219   0.8152   1.0000
   2.750   0.8327   0.01491   0.00715  -0.1214   0.8041   1.0000
   3.000   0.8596   0.01491   0.00722  -0.1207   0.7915   1.0000
   3.250   0.8852   0.01494   0.00735  -0.1198   0.7763   1.0000
   3.500   0.9101   0.01498   0.00750  -0.1188   0.7584   1.0000
   3.750   0.9360   0.01498   0.00764  -0.1178   0.7387   1.0000
   4.000   0.9604   0.01496   0.00773  -0.1165   0.7101   1.0000
   4.250   0.9831   0.01488   0.00760  -0.1145   0.6508   1.0000
   4.500   1.0045   0.01516   0.00721  -0.1118   0.5382   1.0000
   4.750   1.0206   0.01619   0.00766  -0.1093   0.4363   1.0000
   5.000   1.0376   0.01723   0.00827  -0.1074   0.3603   1.0000
   5.250   1.0552   0.01827   0.00898  -0.1057   0.2905   1.0000
   5.500   1.0701   0.01972   0.00980  -0.1039   0.1790   1.0000
   5.750   1.0838   0.02156   0.01099  -0.1019   0.0910   1.0000
   6.000   1.1018   0.02286   0.01220  -0.1004   0.0719   1.0000
   6.250   1.1193   0.02414   0.01354  -0.0987   0.0628   1.0000
   6.500   1.1381   0.02518   0.01473  -0.0972   0.0554   1.0000
   6.750   1.1531   0.02661   0.01621  -0.0953   0.0506   1.0000
   7.000   1.1704   0.02781   0.01761  -0.0936   0.0479   1.0000
   7.250   1.1872   0.02918   0.01913  -0.0917   0.0453   1.0000
   7.500   1.2046   0.03068   0.02074  -0.0901   0.0430   1.0000
   7.750   1.2221   0.03241   0.02249  -0.0887   0.0402   1.0000
   8.000   1.2420   0.03423   0.02446  -0.0875   0.0373   1.0000
   8.250   1.2640   0.03611   0.02667  -0.0865   0.0353   1.0000
   8.500   1.2859   0.03835   0.02919  -0.0854   0.0335   1.0000
   8.750   1.3052   0.04068   0.03181  -0.0841   0.0316   1.0000
   9.000   1.3197   0.04273   0.03398  -0.0828   0.0290   1.0000
   9.250   1.3326   0.04612   0.03772  -0.0810   0.0271   1.0000
   9.500   1.3409   0.04906   0.04123  -0.0782   0.0255   1.0000
   9.750   1.3449   0.05165   0.04428  -0.0752   0.0232   1.0000
  10.000   1.3471   0.05392   0.04684  -0.0724   0.0212   1.0000
  10.250   1.3451   0.05661   0.04980  -0.0692   0.0202   1.0000
  10.500   1.3389   0.05905   0.05239  -0.0659   0.0193   1.0000
  11.000   1.3092   0.06636   0.06028  -0.0591   0.0181   1.0000
  11.250   1.2913   0.07031   0.06459  -0.0567   0.0178   1.0000
  11.500   1.2719   0.07487   0.06947  -0.0552   0.0175   1.0000
  11.750   1.2514   0.08000   0.07488  -0.0549   0.0173   1.0000
  12.000   1.2307   0.08567   0.08078  -0.0557   0.0174   1.0000
  12.250   1.2099   0.09192   0.08724  -0.0576   0.0175   1.0000
  12.500   1.1895   0.09886   0.09435  -0.0608   0.0177   1.0000
  12.750   1.1701   0.10646   0.10209  -0.0651   0.0180   1.0000
  13.000   1.1519   0.11465   0.11038  -0.0700   0.0183   1.0000
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