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HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il)
Reynolds number: 100,000
Max Cl/Cd: 66.51 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1708-il-100000-n5.txt
Download as CSV file: xf-hs1708-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3273   0.11335   0.10834  -0.0369   1.0000   0.0325
  -9.250  -0.3326   0.11147   0.10653  -0.0350   1.0000   0.0320
  -9.000  -0.3409   0.10989   0.10503  -0.0327   1.0000   0.0317
  -8.500  -0.3339   0.10379   0.09899  -0.0355   0.9949   0.0312
  -8.250  -0.3239   0.09992   0.09513  -0.0389   0.9897   0.0309
  -8.000  -0.3132   0.09591   0.09113  -0.0427   0.9851   0.0302
  -7.750  -0.3068   0.09214   0.08738  -0.0457   0.9780   0.0295
  -7.500  -0.2920   0.08724   0.08247  -0.0517   0.9727   0.0288
  -7.250  -0.2814   0.08265   0.07788  -0.0567   0.9651   0.0282
  -7.000  -0.2629   0.07716   0.07238  -0.0642   0.9602   0.0279
  -6.750  -0.2466   0.07219   0.06737  -0.0702   0.9543   0.0279
  -6.500  -0.2252   0.06687   0.06200  -0.0774   0.9490   0.0281
  -6.250  -0.1947   0.06073   0.05576  -0.0866   0.9456   0.0288
  -6.000  -0.1681   0.05468   0.04957  -0.0945   0.9401   0.0304
  -5.750  -0.1171   0.03788   0.03202  -0.1148   0.9362   0.0350
  -5.500  -0.0890   0.03900   0.03316  -0.1151   0.9336   0.0396
  -5.250  -0.0412   0.02950   0.02251  -0.1254   0.9325   0.0468
  -5.000  -0.0027   0.02671   0.01891  -0.1290   0.9311   0.0555
  -4.750   0.0244   0.02615   0.01833  -0.1295   0.9275   0.0599
  -4.500   0.0546   0.02464   0.01624  -0.1305   0.9239   0.0671
  -4.250   0.0854   0.02376   0.01525  -0.1316   0.9214   0.0715
  -4.000   0.1185   0.02297   0.01413  -0.1330   0.9193   0.0787
  -3.750   0.1522   0.02226   0.01329  -0.1344   0.9175   0.0848
  -3.500   0.1869   0.02163   0.01243  -0.1359   0.9159   0.0925
  -3.250   0.2091   0.02147   0.01224  -0.1351   0.9109   0.0990
  -3.000   0.2388   0.02106   0.01165  -0.1356   0.9076   0.1068
  -2.750   0.2703   0.02080   0.01139  -0.1365   0.9051   0.1157
  -2.500   0.3034   0.02050   0.01101  -0.1376   0.9030   0.1265
  -2.250   0.3375   0.02017   0.01059  -0.1389   0.9013   0.1377
  -2.000   0.3586   0.02027   0.01070  -0.1378   0.8949   0.1488
  -1.750   0.3900   0.02009   0.01051  -0.1385   0.8911   0.1622
  -1.500   0.4241   0.01982   0.01022  -0.1396   0.8883   0.1763
  -1.250   0.4516   0.01977   0.01016  -0.1396   0.8833   0.1908
  -1.000   0.4788   0.01971   0.01012  -0.1395   0.8782   0.2045
  -0.750   0.5106   0.01954   0.00996  -0.1402   0.8749   0.2206
  -0.500   0.5442   0.01932   0.00976  -0.1412   0.8724   0.2377
  -0.250   0.5661   0.01942   0.00990  -0.1401   0.8649   0.2524
   0.000   0.5998   0.01906   0.00960  -0.1409   0.8598   0.2718
   0.250   0.6283   0.01882   0.00942  -0.1406   0.8517   0.2932
   0.500   0.6622   0.01829   0.00900  -0.1412   0.8445   0.3271
   0.750   0.6891   0.01761   0.00899  -0.1410   0.8359   0.5053
   1.250   0.7380   0.01677   0.00880  -0.1383   0.8220   1.0000
   1.500   0.7684   0.01672   0.00868  -0.1384   0.8160   1.0000
   1.750   0.7935   0.01686   0.00879  -0.1377   0.8075   1.0000
   2.000   0.8238   0.01678   0.00869  -0.1377   0.8009   1.0000
   2.250   0.8480   0.01691   0.00883  -0.1368   0.7909   1.0000
   2.500   0.8766   0.01686   0.00877  -0.1365   0.7826   1.0000
   2.750   0.9034   0.01684   0.00879  -0.1359   0.7724   1.0000
   3.000   0.9280   0.01689   0.00888  -0.1349   0.7603   1.0000
   3.250   0.9532   0.01691   0.00894  -0.1340   0.7475   1.0000
   3.500   0.9783   0.01692   0.00900  -0.1331   0.7333   1.0000
   3.750   1.0031   0.01693   0.00909  -0.1321   0.7171   1.0000
   4.000   1.0285   0.01689   0.00910  -0.1312   0.6986   1.0000
   4.250   1.0510   0.01696   0.00923  -0.1298   0.6738   1.0000
   4.500   1.0762   0.01692   0.00921  -0.1287   0.6439   1.0000
   4.750   1.1031   0.01687   0.00906  -0.1278   0.6076   1.0000
   5.000   1.1293   0.01698   0.00898  -0.1268   0.5682   1.0000
   5.250   1.1522   0.01739   0.00919  -0.1255   0.5278   1.0000
   5.500   1.1722   0.01800   0.00957  -0.1238   0.4840   1.0000
   5.750   1.1893   0.01877   0.01007  -0.1217   0.4367   1.0000
   6.000   1.2049   0.01962   0.01063  -0.1195   0.3923   1.0000
   6.250   1.2217   0.02042   0.01128  -0.1176   0.3582   1.0000
   6.500   1.2393   0.02118   0.01194  -0.1159   0.3313   1.0000
   6.750   1.2569   0.02190   0.01263  -0.1142   0.3052   1.0000
   7.000   1.2735   0.02266   0.01335  -0.1124   0.2763   1.0000
   7.250   1.2890   0.02348   0.01413  -0.1105   0.2438   1.0000
   7.500   1.3026   0.02443   0.01495  -0.1083   0.2055   1.0000
   7.750   1.3124   0.02569   0.01594  -0.1057   0.1600   1.0000
   8.000   1.3198   0.02714   0.01711  -0.1028   0.1206   1.0000
   8.250   1.3278   0.02854   0.01837  -0.0999   0.0981   1.0000
   8.500   1.3367   0.02989   0.01971  -0.0972   0.0863   1.0000
   8.750   1.3448   0.03131   0.02114  -0.0945   0.0790   1.0000
   9.000   1.3535   0.03268   0.02264  -0.0920   0.0730   1.0000
   9.250   1.3587   0.03433   0.02429  -0.0892   0.0684   1.0000
   9.500   1.3679   0.03571   0.02584  -0.0869   0.0639   1.0000
   9.750   1.3751   0.03727   0.02750  -0.0845   0.0603   1.0000
  10.000   1.3796   0.03910   0.02939  -0.0820   0.0578   1.0000
  10.250   1.3859   0.04092   0.03131  -0.0797   0.0558   1.0000
  10.500   1.3953   0.04255   0.03312  -0.0777   0.0534   1.0000
  10.750   1.4040   0.04426   0.03501  -0.0758   0.0508   1.0000
  11.000   1.4114   0.04606   0.03690  -0.0740   0.0484   1.0000
  11.250   1.4180   0.04807   0.03896  -0.0722   0.0464   1.0000
  11.500   1.4284   0.05015   0.04112  -0.0705   0.0448   1.0000
  11.750   1.4388   0.05213   0.04335  -0.0689   0.0434   1.0000
  12.000   1.4473   0.05426   0.04574  -0.0672   0.0418   1.0000
  12.250   1.4530   0.05652   0.04822  -0.0656   0.0401   1.0000
  12.500   1.4565   0.05886   0.05073  -0.0640   0.0384   1.0000
  12.750   1.4591   0.06129   0.05328  -0.0626   0.0370   1.0000
  13.000   1.4628   0.06395   0.05608  -0.0612   0.0359   1.0000
  13.250   1.4664   0.06723   0.05951  -0.0599   0.0349   1.0000
  13.500   1.4612   0.07066   0.06329  -0.0585   0.0343   1.0000
  13.750   1.4529   0.07447   0.06744  -0.0574   0.0335   1.0000
  14.000   1.4421   0.07865   0.07193  -0.0566   0.0328   1.0000
  14.250   1.4295   0.08317   0.07675  -0.0564   0.0320   1.0000
  14.500   1.4153   0.08803   0.08189  -0.0567   0.0314   1.0000
  14.750   1.3998   0.09338   0.08750  -0.0577   0.0308   1.0000
  15.000   1.3830   0.09932   0.09371  -0.0595   0.0304   1.0000
  15.250   1.3646   0.10597   0.10061  -0.0621   0.0301   1.0000
  15.500   1.3441   0.11359   0.10847  -0.0659   0.0300   1.0000
  15.750   1.3206   0.12255   0.11768  -0.0711   0.0300   1.0000
  16.000   1.2904   0.13408   0.12947  -0.0787   0.0305   1.0000
  16.250   1.2471   0.15083   0.14642  -0.0904   0.0318   1.0000
  16.500   1.2003   0.17173   0.16741  -0.1047   0.0333   1.0000
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