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HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il)
Reynolds number: 200,000
Max Cl/Cd: 90.73 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1606-il-200000-n5.txt
Download as CSV file: xf-hs1606-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3551   0.10437   0.10081  -0.0329   1.0000   0.0215
  -8.500  -0.3547   0.10182   0.09832  -0.0331   1.0000   0.0216
  -8.250  -0.3567   0.09951   0.09607  -0.0325   1.0000   0.0217
  -7.250  -0.3319   0.08405   0.08070  -0.0378   0.9878   0.0126
  -7.000  -0.3100   0.07912   0.07576  -0.0447   0.9832   0.0116
  -6.750  -0.2886   0.07362   0.07025  -0.0523   0.9755   0.0106
  -6.500  -0.2567   0.06489   0.06147  -0.0650   0.9702   0.0091
  -6.250  -0.2290   0.05967   0.05618  -0.0724   0.9630   0.0088
  -6.000  -0.1945   0.05292   0.04933  -0.0827   0.9583   0.0087
  -5.750  -0.1552   0.04469   0.04092  -0.0942   0.9528   0.0086
  -5.500  -0.0986   0.02765   0.02299  -0.1127   0.9483   0.0083
  -5.250  -0.0589   0.02236   0.01677  -0.1179   0.9454   0.0088
  -5.000  -0.0243   0.01953   0.01348  -0.1208   0.9431   0.0105
  -4.750   0.0062   0.01793   0.01151  -0.1219   0.9385   0.0115
  -4.500   0.0382   0.01640   0.00962  -0.1229   0.9348   0.0117
  -4.250   0.0707   0.01526   0.00821  -0.1239   0.9317   0.0120
  -4.000   0.1027   0.01440   0.00709  -0.1248   0.9285   0.0125
  -3.750   0.1322   0.01378   0.00626  -0.1251   0.9236   0.0132
  -3.500   0.1630   0.01324   0.00553  -0.1256   0.9200   0.0143
  -3.250   0.1943   0.01260   0.00477  -0.1262   0.9172   0.0202
  -3.000   0.2231   0.01208   0.00444  -0.1265   0.9128   0.0694
  -2.750   0.2519   0.01196   0.00441  -0.1269   0.9086   0.1075
  -2.500   0.2815   0.01182   0.00422  -0.1272   0.9055   0.1219
  -2.250   0.3107   0.01169   0.00406  -0.1274   0.9020   0.1340
  -2.000   0.3386   0.01163   0.00398  -0.1274   0.8973   0.1479
  -1.750   0.3674   0.01156   0.00388  -0.1276   0.8935   0.1618
  -1.500   0.3965   0.01147   0.00376  -0.1277   0.8900   0.1735
  -1.250   0.4235   0.01143   0.00371  -0.1275   0.8830   0.1851
  -1.000   0.4518   0.01133   0.00359  -0.1274   0.8770   0.1972
  -0.750   0.4787   0.01127   0.00352  -0.1270   0.8691   0.2084
  -0.500   0.5067   0.01118   0.00341  -0.1268   0.8625   0.2204
   0.000   0.5609   0.01103   0.00331  -0.1262   0.8460   0.2457
   0.250   0.5879   0.01095   0.00327  -0.1259   0.8372   0.2598
   0.500   0.6153   0.01087   0.00327  -0.1257   0.8295   0.2771
   0.750   0.6429   0.01076   0.00328  -0.1256   0.8231   0.3072
   1.000   0.6611   0.00943   0.00339  -0.1233   0.8166   0.8701
   1.250   0.6900   0.00940   0.00338  -0.1234   0.8092   1.0000
   1.500   0.7173   0.00947   0.00342  -0.1231   0.8010   1.0000
   1.750   0.7448   0.00954   0.00345  -0.1228   0.7929   1.0000
   2.000   0.7717   0.00961   0.00354  -0.1225   0.7826   1.0000
   2.250   0.7987   0.00969   0.00362  -0.1222   0.7717   1.0000
   2.500   0.8255   0.00976   0.00374  -0.1218   0.7590   1.0000
   2.750   0.8520   0.00983   0.00383  -0.1213   0.7439   1.0000
   3.000   0.8784   0.00990   0.00392  -0.1208   0.7261   1.0000
   3.250   0.9040   0.00998   0.00397  -0.1200   0.6966   1.0000
   3.500   0.9264   0.01021   0.00391  -0.1183   0.6159   1.0000
   3.750   0.9441   0.01105   0.00411  -0.1161   0.5123   1.0000
   4.000   0.9632   0.01191   0.00454  -0.1145   0.4306   1.0000
   4.250   0.9826   0.01277   0.00503  -0.1131   0.3597   1.0000
   4.500   1.0027   0.01361   0.00554  -0.1119   0.2964   1.0000
   4.750   1.0236   0.01439   0.00608  -0.1109   0.2362   1.0000
   5.000   1.0423   0.01546   0.00672  -0.1096   0.1537   1.0000
   5.250   1.0591   0.01685   0.00761  -0.1081   0.0744   1.0000
   5.500   1.0801   0.01769   0.00838  -0.1071   0.0555   1.0000
   5.750   1.1020   0.01841   0.00913  -0.1061   0.0468   1.0000
   6.000   1.1234   0.01915   0.00994  -0.1050   0.0417   1.0000
   6.250   1.1433   0.02007   0.01097  -0.1037   0.0382   1.0000
   6.500   1.1640   0.02084   0.01188  -0.1025   0.0361   1.0000
   6.750   1.1838   0.02169   0.01285  -0.1012   0.0337   1.0000
   7.000   1.2033   0.02255   0.01378  -0.0999   0.0310   1.0000
   7.250   1.2196   0.02379   0.01507  -0.0982   0.0286   1.0000
   7.500   1.2358   0.02519   0.01657  -0.0964   0.0274   1.0000
   7.750   1.2545   0.02629   0.01782  -0.0949   0.0264   1.0000
   8.000   1.2730   0.02757   0.01930  -0.0934   0.0253   1.0000
   8.250   1.2917   0.02887   0.02077  -0.0919   0.0238   1.0000
   8.500   1.3098   0.02993   0.02197  -0.0906   0.0219   1.0000
   8.750   1.3266   0.03114   0.02330  -0.0891   0.0204   1.0000
   9.000   1.3406   0.03353   0.02580  -0.0874   0.0185   1.0000
   9.250   1.3570   0.03395   0.02649  -0.0857   0.0167   1.0000
   9.500   1.3713   0.03476   0.02750  -0.0839   0.0145   1.0000
   9.750   1.3823   0.03545   0.02830  -0.0817   0.0130   1.0000
  10.000   1.3880   0.03689   0.02985  -0.0789   0.0118   1.0000
  10.250   1.3964   0.03886   0.03215  -0.0763   0.0103   1.0000
  10.500   1.4045   0.04015   0.03372  -0.0739   0.0088   1.0000
  10.750   1.4131   0.04073   0.03437  -0.0719   0.0077   1.0000
  11.000   1.4164   0.04226   0.03601  -0.0697   0.0070   1.0000
  11.250   1.4148   0.04532   0.03941  -0.0668   0.0065   1.0000
  11.500   1.4095   0.04875   0.04321  -0.0639   0.0061   1.0000
  11.750   1.4011   0.05246   0.04727  -0.0613   0.0057   1.0000
  12.000   1.3900   0.05646   0.05159  -0.0592   0.0055   1.0000
  12.250   1.3765   0.06085   0.05628  -0.0577   0.0054   1.0000
  12.500   1.3608   0.06570   0.06142  -0.0569   0.0052   1.0000
  12.750   1.3423   0.07125   0.06724  -0.0569   0.0052   1.0000
  13.000   1.3212   0.07766   0.07392  -0.0582   0.0052   1.0000
  13.250   1.2977   0.08516   0.08168  -0.0608   0.0052   1.0000
  13.500   1.2729   0.09389   0.09064  -0.0651   0.0053   1.0000
  13.750   1.2476   0.10399   0.10096  -0.0712   0.0054   1.0000
  14.000   1.2221   0.11545   0.11259  -0.0785   0.0057   1.0000
  14.250   1.1971   0.12799   0.12525  -0.0865   0.0060   1.0000
  14.500   1.1739   0.14074   0.13806  -0.0940   0.0064   1.0000
  14.750   1.1503   0.15420   0.15147  -0.1012   0.0068   1.0000
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