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HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il)
Reynolds number: 100,000
Max Cl/Cd: 68.47 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1606-il-100000.txt
Download as CSV file: xf-hs1606-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3567   0.10276   0.09798  -0.0301   1.0000   0.0669
  -7.750  -0.3710   0.10245   0.09781  -0.0288   1.0000   0.0675
  -7.500  -0.3826   0.10198   0.09746  -0.0293   1.0000   0.0678
  -7.250  -0.3904   0.10113   0.09670  -0.0310   1.0000   0.0681
  -7.000  -0.3928   0.09969   0.09530  -0.0339   1.0000   0.0683
  -6.750  -0.3863   0.09264   0.08830  -0.0214   1.0000   0.0719
  -6.500  -0.3891   0.09066   0.08637  -0.0199   1.0000   0.0740
  -6.250  -0.3910   0.08861   0.08436  -0.0197   1.0000   0.0764
  -6.000  -0.3892   0.08652   0.08232  -0.0224   1.0000   0.0796
  -5.750  -0.3664   0.08438   0.08008  -0.0379   1.0000   0.0817
  -5.500  -0.3725   0.07990   0.07571  -0.0301   1.0000   0.0830
  -5.250  -0.3683   0.07686   0.07270  -0.0275   1.0000   0.0848
  -5.000  -0.3578   0.07387   0.06971  -0.0281   1.0000   0.0878
  -4.750  -0.3118   0.06942   0.06501  -0.0447   1.0000   0.0955
  -4.500  -0.3075   0.06563   0.06130  -0.0414   1.0000   0.0967
  -4.250  -0.2948   0.06253   0.05821  -0.0407   1.0000   0.0993
  -3.750  -0.2299   0.05428   0.04963  -0.0525   1.0000   0.1108
  -3.500  -0.1600   0.04243   0.03718  -0.0665   1.0000   0.0606
  -3.250  -0.0727   0.02911   0.02228  -0.0818   1.0000   0.0470
  -3.000  -0.0259   0.02500   0.01722  -0.0858   1.0000   0.0479
  -2.750   0.0117   0.02297   0.01459  -0.0875   1.0000   0.0535
  -2.500   0.0438   0.02199   0.01353  -0.0886   1.0000   0.0748
  -2.250   0.0589   0.02373   0.01558  -0.0868   1.0000   0.1387
  -2.000   0.0820   0.02411   0.01575  -0.0863   1.0000   0.1635
  -1.750   0.1084   0.02382   0.01527  -0.0865   1.0000   0.1781
  -1.500   0.1356   0.02345   0.01474  -0.0869   1.0000   0.1905
  -1.250   0.1630   0.02316   0.01429  -0.0873   1.0000   0.2045
  -1.000   0.1893   0.02298   0.01409  -0.0876   1.0000   0.2224
  -0.750   0.2161   0.02280   0.01386  -0.0880   1.0000   0.2403
  -0.500   0.2485   0.02268   0.01368  -0.0895   0.9983   0.2638
  -0.250   0.2926   0.02255   0.01358  -0.0932   0.9945   0.2926
   0.000   0.3315   0.02241   0.01355  -0.0960   0.9890   0.3220
   0.250   0.3776   0.02235   0.01358  -0.1000   0.9842   0.3603
   0.500   0.4232   0.02202   0.01363  -0.1040   0.9755   0.4316
   0.750   0.4631   0.02093   0.01355  -0.1060   0.9647   1.0000
   1.000   0.5120   0.02114   0.01356  -0.1101   0.9544   1.0000
   1.250   0.5516   0.02136   0.01368  -0.1125   0.9448   1.0000
   1.500   0.5866   0.02161   0.01388  -0.1141   0.9347   1.0000
   1.750   0.6259   0.02177   0.01403  -0.1164   0.9255   1.0000
   2.000   0.6704   0.02178   0.01409  -0.1195   0.9172   1.0000
   2.250   0.7052   0.02185   0.01420  -0.1207   0.9059   1.0000
   2.500   0.7413   0.02182   0.01424  -0.1220   0.8943   1.0000
   2.750   0.7803   0.02164   0.01416  -0.1235   0.8829   1.0000
   3.000   0.8244   0.02120   0.01391  -0.1257   0.8729   1.0000
   3.250   0.8679   0.02055   0.01341  -0.1274   0.8626   1.0000
   3.500   0.9031   0.02001   0.01303  -0.1274   0.8490   1.0000
   3.750   0.9377   0.01938   0.01262  -0.1271   0.8347   1.0000
   4.000   0.9646   0.01887   0.01228  -0.1253   0.8143   1.0000
   4.250   0.9955   0.01760   0.01115  -0.1229   0.7873   1.0000
   4.500   1.0210   0.01643   0.01004  -0.1195   0.7477   1.0000
   4.750   1.0424   0.01581   0.00949  -0.1163   0.6930   1.0000
   5.000   1.0647   0.01555   0.00906  -0.1134   0.6149   1.0000
   5.250   1.0827   0.01616   0.00901  -0.1102   0.5059   1.0000
   5.500   1.0939   0.01754   0.00969  -0.1067   0.3846   1.0000
   5.750   1.0926   0.02060   0.01112  -0.1020   0.1604   1.0000
   6.000   1.1032   0.02287   0.01284  -0.0991   0.1149   1.0000
   6.250   1.1189   0.02444   0.01437  -0.0970   0.0986   1.0000
   6.500   1.1344   0.02622   0.01608  -0.0949   0.0888   1.0000
   6.750   1.1561   0.02775   0.01773  -0.0935   0.0830   1.0000
   7.000   1.1807   0.02978   0.01968  -0.0927   0.0781   1.0000
   7.250   1.2101   0.03232   0.02230  -0.0925   0.0744   1.0000
   7.500   1.2348   0.03414   0.02436  -0.0917   0.0690   1.0000
   7.750   1.2620   0.03682   0.02723  -0.0912   0.0663   1.0000
   8.000   1.2883   0.04046   0.03112  -0.0907   0.0647   1.0000
   8.250   1.3084   0.04530   0.03645  -0.0894   0.0633   1.0000
   8.500   1.3188   0.04726   0.03913  -0.0861   0.0607   1.0000
   8.750   1.3292   0.05157   0.04402  -0.0832   0.0606   1.0000
   9.000   1.3340   0.05615   0.04917  -0.0799   0.0606   1.0000
   9.250   1.3323   0.06020   0.05376  -0.0762   0.0590   1.0000
   9.500   1.3265   0.06475   0.05879  -0.0725   0.0586   1.0000
   9.750   1.3185   0.07037   0.06475  -0.0693   0.0608   1.0000
  10.000   1.2166   0.06560   0.06044  -0.0533   0.0608   1.0000
  10.250   1.1967   0.07006   0.06508  -0.0494   0.0616   1.0000
  10.500   1.1413   0.07539   0.07093  -0.0441   0.0710   1.0000
  10.750   1.1145   0.08083   0.07651  -0.0425   0.0731   1.0000
  11.000   1.0925   0.08648   0.08226  -0.0417   0.0744   1.0000
  11.250   1.0831   0.09292   0.08874  -0.0414   0.0755   1.0000
  11.500   0.9961   0.10149   0.09758  -0.0473   0.0800   1.0000
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