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HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il)
Reynolds number: 500,000
Max Cl/Cd: 139.47 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1708-il-500000.txt
Download as CSV file: xf-hs1708-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-708 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2187   0.08416   0.08190  -0.0677   0.9738   0.0248
  -8.000  -0.2071   0.07950   0.07724  -0.0750   0.9610   0.0259
  -7.750  -0.2239   0.02042   0.01638  -0.1379   0.9338   0.0126
  -7.500  -0.1961   0.01811   0.01366  -0.1394   0.9294   0.0127
  -7.250  -0.1685   0.01658   0.01183  -0.1402   0.9239   0.0130
  -7.000  -0.1404   0.01537   0.01038  -0.1407   0.9194   0.0135
  -6.750  -0.1120   0.01440   0.00917  -0.1411   0.9156   0.0140
  -6.500  -0.0836   0.01360   0.00818  -0.1414   0.9108   0.0147
  -6.250  -0.0549   0.01265   0.00705  -0.1419   0.9065   0.0159
  -6.000  -0.0262   0.01210   0.00639  -0.1421   0.9030   0.0178
  -5.750   0.0029   0.01148   0.00566  -0.1425   0.8996   0.0217
  -5.500   0.0317   0.01108   0.00525  -0.1428   0.8959   0.0303
  -5.250   0.0604   0.01091   0.00503  -0.1429   0.8924   0.0371
  -5.000   0.0889   0.01091   0.00499  -0.1430   0.8892   0.0422
  -4.750   0.1176   0.01067   0.00469  -0.1432   0.8862   0.0469
  -4.500   0.1464   0.01055   0.00454  -0.1435   0.8829   0.0514
  -4.250   0.1752   0.01052   0.00444  -0.1436   0.8798   0.0550
  -4.000   0.2041   0.01021   0.00414  -0.1439   0.8769   0.0617
  -3.750   0.2329   0.01011   0.00397  -0.1441   0.8742   0.0664
  -3.500   0.2618   0.00990   0.00374  -0.1443   0.8716   0.0726
  -3.250   0.2906   0.00983   0.00366  -0.1445   0.8686   0.0793
  -3.000   0.3192   0.00965   0.00350  -0.1447   0.8648   0.0875
  -2.750   0.3476   0.00958   0.00336  -0.1447   0.8604   0.0944
  -2.500   0.3759   0.00942   0.00322  -0.1447   0.8558   0.1050
  -2.250   0.4042   0.00928   0.00311  -0.1447   0.8502   0.1162
  -2.000   0.4326   0.00917   0.00300  -0.1446   0.8453   0.1283
  -1.750   0.4611   0.00914   0.00296  -0.1447   0.8413   0.1414
  -1.500   0.4895   0.00909   0.00293  -0.1448   0.8369   0.1539
  -1.250   0.5180   0.00906   0.00290  -0.1448   0.8325   0.1652
  -1.000   0.5465   0.00903   0.00286  -0.1448   0.8284   0.1760
  -0.750   0.5747   0.00897   0.00285  -0.1448   0.8231   0.1870
  -0.500   0.6031   0.00895   0.00281  -0.1448   0.8183   0.1975
  -0.250   0.6317   0.00892   0.00280  -0.1449   0.8146   0.2080
   0.000   0.6601   0.00888   0.00282  -0.1450   0.8103   0.2194
   0.250   0.6886   0.00883   0.00281  -0.1451   0.8054   0.2310
   0.500   0.7171   0.00878   0.00279  -0.1451   0.8009   0.2447
   0.750   0.7453   0.00872   0.00280  -0.1451   0.7954   0.2614
   1.000   0.7736   0.00862   0.00279  -0.1452   0.7896   0.2848
   1.250   0.8024   0.00843   0.00281  -0.1454   0.7847   0.3591
   1.500   0.8228   0.00712   0.00289  -0.1438   0.7785   1.0000
   1.750   0.8510   0.00716   0.00288  -0.1437   0.7722   1.0000
   2.000   0.8789   0.00719   0.00290  -0.1436   0.7643   1.0000
   2.250   0.9067   0.00722   0.00288  -0.1434   0.7560   1.0000
   2.500   0.9342   0.00723   0.00291  -0.1433   0.7453   1.0000
   2.750   0.9617   0.00727   0.00294  -0.1431   0.7343   1.0000
   3.000   0.9891   0.00732   0.00297  -0.1428   0.7215   1.0000
   3.250   1.0160   0.00737   0.00302  -0.1425   0.7049   1.0000
   3.500   1.0418   0.00747   0.00304  -0.1419   0.6742   1.0000
   3.750   1.0632   0.00787   0.00309  -0.1404   0.6044   1.0000
   4.000   1.0827   0.00856   0.00341  -0.1388   0.5383   1.0000
   4.250   1.1032   0.00922   0.00377  -0.1374   0.4812   1.0000
   4.500   1.1239   0.00986   0.00414  -0.1362   0.4256   1.0000
   4.750   1.1456   0.01041   0.00449  -0.1351   0.3869   1.0000
   5.000   1.1682   0.01090   0.00484  -0.1343   0.3583   1.0000
   5.250   1.1910   0.01135   0.00518  -0.1334   0.3344   1.0000
   5.500   1.2144   0.01174   0.00550  -0.1327   0.3147   1.0000
   5.750   1.2377   0.01213   0.00584  -0.1319   0.2945   1.0000
   6.000   1.2603   0.01256   0.00619  -0.1310   0.2726   1.0000
   6.250   1.2820   0.01305   0.00656  -0.1301   0.2441   1.0000
   6.500   1.3016   0.01371   0.00702  -0.1287   0.2041   1.0000
   6.750   1.3175   0.01467   0.00766  -0.1268   0.1503   1.0000
   7.000   1.3297   0.01594   0.00854  -0.1244   0.0912   1.0000
   7.250   1.3455   0.01689   0.00933  -0.1224   0.0683   1.0000
   7.500   1.3631   0.01763   0.01003  -0.1207   0.0591   1.0000
   7.750   1.3816   0.01824   0.01068  -0.1191   0.0539   1.0000
   8.000   1.3989   0.01890   0.01137  -0.1173   0.0496   1.0000
   8.250   1.4103   0.01993   0.01244  -0.1145   0.0453   1.0000
   8.500   1.4268   0.02045   0.01304  -0.1125   0.0438   1.0000
   8.750   1.4419   0.02110   0.01376  -0.1104   0.0418   1.0000
   9.000   1.4565   0.02180   0.01451  -0.1083   0.0397   1.0000
   9.250   1.4681   0.02273   0.01548  -0.1058   0.0375   1.0000
   9.500   1.4707   0.02436   0.01720  -0.1020   0.0352   1.0000
   9.750   1.4844   0.02519   0.01813  -0.1000   0.0344   1.0000
  10.000   1.4981   0.02604   0.01907  -0.0981   0.0334   1.0000
  10.250   1.5103   0.02702   0.02015  -0.0960   0.0322   1.0000
  10.500   1.5223   0.02803   0.02123  -0.0940   0.0309   1.0000
  10.750   1.5339   0.02907   0.02233  -0.0921   0.0296   1.0000
  11.000   1.5431   0.03033   0.02365  -0.0900   0.0284   1.0000
  11.250   1.5442   0.03238   0.02578  -0.0870   0.0270   1.0000
  11.500   1.5472   0.03436   0.02789  -0.0843   0.0260   1.0000
  11.750   1.5616   0.03518   0.02881  -0.0831   0.0252   1.0000
  12.000   1.5734   0.03628   0.03001  -0.0817   0.0241   1.0000
  12.250   1.5844   0.03745   0.03127  -0.0803   0.0229   1.0000
  12.500   1.5944   0.03873   0.03261  -0.0789   0.0219   1.0000
  12.750   1.6022   0.04024   0.03418  -0.0774   0.0210   1.0000
  13.000   1.6030   0.04250   0.03651  -0.0754   0.0201   1.0000
  13.250   1.5927   0.04600   0.04017  -0.0725   0.0191   1.0000
  13.500   1.6016   0.04750   0.04178  -0.0715   0.0187   1.0000
  13.750   1.6083   0.04929   0.04370  -0.0704   0.0181   1.0000
  14.000   1.6133   0.05128   0.04582  -0.0693   0.0173   1.0000
  14.250   1.6180   0.05337   0.04802  -0.0684   0.0165   1.0000
  14.500   1.6227   0.05550   0.05024  -0.0677   0.0157   1.0000
  14.750   1.6262   0.05786   0.05266  -0.0672   0.0150   1.0000
  15.000   1.6213   0.06132   0.05620  -0.0665   0.0143   1.0000
  15.250   1.6050   0.06633   0.06136  -0.0656   0.0136   1.0000
  15.500   1.6092   0.06900   0.06418  -0.0657   0.0131   1.0000
  15.750   1.6098   0.07223   0.06755  -0.0659   0.0125   1.0000
  16.000   1.6085   0.07583   0.07127  -0.0664   0.0119   1.0000
  16.250   1.6061   0.07974   0.07529  -0.0671   0.0113   1.0000
  16.500   1.6017   0.08408   0.07973  -0.0682   0.0109   1.0000
  16.750   1.5947   0.08895   0.08471  -0.0696   0.0105   1.0000
  17.000   1.5811   0.09493   0.09081  -0.0714   0.0101   1.0000
  17.250   1.5633   0.10172   0.09775  -0.0736   0.0098   1.0000
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