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HAM-STD HS1-712 AIRFOIL (hs1712-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-712 AIRFOIL (hs1712-il)
Reynolds number: 200,000
Max Cl/Cd: 82.8 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1712-il-200000.txt
Download as CSV file: xf-hs1712-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-712 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.4249   0.09634   0.09318  -0.0285   0.9933   0.0564
  -7.000  -0.4057   0.09189   0.08872  -0.0346   0.9877   0.0597
  -6.750  -0.3803   0.08480   0.08158  -0.0458   0.9832   0.0622
  -6.500  -0.3542   0.07855   0.07525  -0.0560   0.9761   0.0668
  -6.250  -0.3269   0.07340   0.07004  -0.0621   0.9726   0.0690
  -6.000  -0.2686   0.04011   0.03485  -0.0954   0.9719   0.0501
  -5.750  -0.2316   0.03545   0.02966  -0.0995   0.9688   0.0498
  -5.500  -0.1914   0.03136   0.02478  -0.1034   0.9660   0.0498
  -5.250  -0.1521   0.02954   0.02273  -0.1065   0.9629   0.0513
  -5.000  -0.1093   0.02818   0.02094  -0.1098   0.9606   0.0548
  -4.750  -0.0663   0.02698   0.01962  -0.1132   0.9590   0.0575
  -4.500  -0.0332   0.02605   0.01834  -0.1143   0.9529   0.0609
  -4.250   0.0046   0.02523   0.01756  -0.1166   0.9493   0.0652
  -4.000   0.0459   0.02437   0.01663  -0.1195   0.9470   0.0700
  -3.750   0.0887   0.02372   0.01595  -0.1226   0.9452   0.0768
  -3.500   0.1196   0.02325   0.01543  -0.1233   0.9379   0.0829
  -3.250   0.1588   0.02264   0.01489  -0.1257   0.9339   0.0907
  -3.000   0.2010   0.02202   0.01431  -0.1287   0.9314   0.0996
  -2.750   0.2447   0.02145   0.01380  -0.1320   0.9296   0.1123
  -2.500   0.2723   0.02103   0.01346  -0.1320   0.9206   0.1272
  -2.250   0.3132   0.02046   0.01303  -0.1346   0.9173   0.1630
  -2.000   0.3554   0.01998   0.01264  -0.1375   0.9148   0.1996
  -1.750   0.3851   0.01973   0.01239  -0.1378   0.9067   0.2235
  -1.500   0.4232   0.01918   0.01194  -0.1399   0.9020   0.2480
  -1.250   0.4657   0.01850   0.01134  -0.1428   0.8993   0.2746
  -1.000   0.5101   0.01770   0.01070  -0.1461   0.8975   0.3121
  -0.750   0.5369   0.01720   0.01052  -0.1459   0.8869   0.3774
  -0.500   0.5649   0.01543   0.01025  -0.1449   0.8844   0.8553
  -0.250   0.6019   0.01439   0.00917  -0.1458   0.8812   1.0000
   0.000   0.6273   0.01420   0.00889  -0.1449   0.8696   1.0000
   0.250   0.6725   0.01357   0.00815  -0.1481   0.8656   1.0000
   0.500   0.7026   0.01329   0.00780  -0.1482   0.8538   1.0000
   0.750   0.7471   0.01272   0.00713  -0.1513   0.8473   1.0000
   1.000   0.7813   0.01247   0.00680  -0.1523   0.8348   1.0000
   1.250   0.8178   0.01224   0.00649  -0.1539   0.8218   1.0000
   1.500   0.8543   0.01206   0.00622  -0.1555   0.8077   1.0000
   1.750   0.8920   0.01193   0.00597  -0.1574   0.7933   1.0000
   2.000   0.9263   0.01193   0.00585  -0.1585   0.7769   1.0000
   2.250   0.9462   0.01210   0.00600  -0.1567   0.7517   1.0000
   2.500   0.9800   0.01211   0.00582  -0.1577   0.7332   1.0000
   2.750   1.0104   0.01229   0.00584  -0.1580   0.7135   1.0000
   3.000   1.0377   0.01257   0.00599  -0.1578   0.6934   1.0000
   3.250   1.0629   0.01285   0.00619  -0.1571   0.6725   1.0000
   3.500   1.0872   0.01313   0.00638  -0.1563   0.6513   1.0000
   3.750   1.1105   0.01342   0.00657  -0.1552   0.6287   1.0000
   4.000   1.1316   0.01371   0.00679  -0.1537   0.6028   1.0000
   4.250   1.1513   0.01407   0.00699  -0.1519   0.5731   1.0000
   4.500   1.1696   0.01448   0.00728  -0.1498   0.5397   1.0000
   4.750   1.1861   0.01497   0.00756  -0.1474   0.5039   1.0000
   5.000   1.2020   0.01552   0.00792  -0.1450   0.4705   1.0000
   5.250   1.2190   0.01609   0.00833  -0.1428   0.4437   1.0000
   5.500   1.2370   0.01665   0.00877  -0.1409   0.4215   1.0000
   5.750   1.2557   0.01719   0.00921  -0.1392   0.4036   1.0000
   6.000   1.2746   0.01773   0.00967  -0.1376   0.3880   1.0000
   6.250   1.2930   0.01830   0.01015  -0.1359   0.3738   1.0000
   6.500   1.3109   0.01887   0.01065  -0.1341   0.3614   1.0000
   6.750   1.3300   0.01943   0.01117  -0.1325   0.3507   1.0000
   7.000   1.3500   0.02009   0.01174  -0.1312   0.3412   1.0000
   7.250   1.3692   0.02059   0.01231  -0.1297   0.3310   1.0000
   7.500   1.3879   0.02115   0.01288  -0.1281   0.3211   1.0000
   7.750   1.4052   0.02167   0.01343  -0.1263   0.3110   1.0000
   8.000   1.4228   0.02212   0.01398  -0.1245   0.3008   1.0000
   8.250   1.4382   0.02269   0.01454  -0.1224   0.2909   1.0000
   8.500   1.4545   0.02319   0.01511  -0.1204   0.2801   1.0000
   8.750   1.4697   0.02379   0.01575  -0.1183   0.2698   1.0000
   9.000   1.4835   0.02447   0.01644  -0.1161   0.2591   1.0000
   9.250   1.4988   0.02511   0.01716  -0.1141   0.2477   1.0000
   9.500   1.5117   0.02589   0.01795  -0.1118   0.2367   1.0000
   9.750   1.5236   0.02673   0.01880  -0.1094   0.2246   1.0000
  10.000   1.5360   0.02758   0.01970  -0.1071   0.2113   1.0000
  10.250   1.5465   0.02858   0.02071  -0.1047   0.1975   1.0000
  10.500   1.5552   0.02972   0.02183  -0.1020   0.1834   1.0000
  10.750   1.5627   0.03100   0.02309  -0.0993   0.1705   1.0000
  11.250   1.5768   0.03376   0.02585  -0.0941   0.1490   1.0000
  11.500   1.5831   0.03528   0.02737  -0.0916   0.1415   1.0000
  11.750   1.5904   0.03674   0.02887  -0.0892   0.1349   1.0000
  12.000   1.5953   0.03843   0.03055  -0.0868   0.1299   1.0000
  12.250   1.6045   0.03983   0.03207  -0.0849   0.1250   1.0000
  12.500   1.6104   0.04150   0.03377  -0.0828   0.1210   1.0000
  12.750   1.6155   0.04329   0.03558  -0.0806   0.1174   1.0000
  13.000   1.6237   0.04484   0.03729  -0.0790   0.1133   1.0000
  13.250   1.6288   0.04668   0.03919  -0.0772   0.1096   1.0000
  13.500   1.6325   0.04872   0.04124  -0.0754   0.1063   1.0000
  13.750   1.6388   0.05059   0.04328  -0.0739   0.1028   1.0000
  14.000   1.6424   0.05271   0.04548  -0.0725   0.0994   1.0000
  14.250   1.6441   0.05506   0.04783  -0.0709   0.0962   1.0000
  14.500   1.6475   0.05737   0.05034  -0.0698   0.0927   1.0000
  14.750   1.6482   0.05999   0.05303  -0.0686   0.0893   1.0000
  15.000   1.6482   0.06278   0.05591  -0.0676   0.0858   1.0000
  15.250   1.6475   0.06574   0.05901  -0.0668   0.0822   1.0000
  15.500   1.6452   0.06884   0.06212  -0.0660   0.0790   1.0000
  15.750   1.6425   0.07212   0.06550  -0.0653   0.0757   1.0000
  16.000   1.6421   0.07492   0.06821  -0.0643   0.0725   1.0000
  16.250   1.6369   0.07869   0.07218  -0.0640   0.0694   1.0000
  16.500   1.6386   0.08126   0.07468  -0.0632   0.0664   1.0000
  16.750   1.6297   0.08580   0.07952  -0.0636   0.0638   1.0000
  17.000   1.6280   0.08913   0.08290  -0.0637   0.0614   1.0000
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