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HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il)
Reynolds number: 1,000,000
Max Cl/Cd: 160.46 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1606-il-1000000.txt
Download as CSV file: xf-hs1606-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3547   0.09743   0.09582  -0.0311   1.0000   0.0059
  -8.500  -0.3535   0.09497   0.09339  -0.0309   1.0000   0.0060
  -8.250  -0.3527   0.09257   0.09102  -0.0308   0.9995   0.0061
  -8.000  -0.3368   0.08863   0.08708  -0.0353   0.9966   0.0063
  -7.750  -0.3200   0.08455   0.08299  -0.0403   0.9928   0.0065
  -7.500  -0.3014   0.08026   0.07870  -0.0460   0.9865   0.0067
  -7.250  -0.2803   0.07572   0.07416  -0.0526   0.9791   0.0070
  -7.000  -0.2582   0.07101   0.06943  -0.0596   0.9693   0.0073
  -6.750  -0.2378   0.06631   0.06470  -0.0660   0.9554   0.0077
  -6.500  -0.2156   0.06150   0.05983  -0.0723   0.9412   0.0083
  -6.250  -0.1898   0.05719   0.05545  -0.0782   0.9294   0.0088
  -6.000  -0.1617   0.05184   0.05002  -0.0855   0.9182   0.0088
  -4.750   0.0190   0.01191   0.00739  -0.1215   0.8861   0.0057
  -4.500   0.0486   0.01071   0.00595  -0.1218   0.8815   0.0057
  -4.250   0.0780   0.00949   0.00452  -0.1223   0.8773   0.0065
  -4.000   0.1071   0.00901   0.00395  -0.1225   0.8730   0.0072
  -3.750   0.1362   0.00857   0.00340  -0.1228   0.8689   0.0076
  -3.500   0.1651   0.00822   0.00296  -0.1229   0.8648   0.0080
  -3.250   0.1938   0.00801   0.00268  -0.1230   0.8605   0.0087
  -3.000   0.2227   0.00771   0.00231  -0.1231   0.8551   0.0089
  -2.750   0.2514   0.00746   0.00191  -0.1231   0.8494   0.0092
  -2.500   0.2802   0.00729   0.00165  -0.1232   0.8435   0.0103
  -2.250   0.3091   0.00688   0.00142  -0.1234   0.8378   0.0596
  -2.000   0.3376   0.00670   0.00134  -0.1236   0.8325   0.0976
  -1.750   0.3661   0.00660   0.00130  -0.1237   0.8272   0.1215
  -1.500   0.3945   0.00655   0.00127  -0.1238   0.8223   0.1406
  -1.250   0.4229   0.00651   0.00128  -0.1239   0.8169   0.1587
  -1.000   0.4514   0.00648   0.00125  -0.1240   0.8119   0.1677
  -0.750   0.4797   0.00649   0.00123  -0.1240   0.8077   0.1767
  -0.500   0.5083   0.00645   0.00123  -0.1241   0.8033   0.1857
  -0.250   0.5367   0.00643   0.00122  -0.1242   0.7984   0.1928
   0.000   0.5650   0.00643   0.00122  -0.1243   0.7937   0.2012
   0.250   0.5935   0.00640   0.00122  -0.1244   0.7886   0.2097
   0.500   0.6219   0.00639   0.00123  -0.1245   0.7830   0.2190
   0.750   0.6501   0.00638   0.00124  -0.1245   0.7771   0.2305
   1.000   0.6784   0.00634   0.00126  -0.1246   0.7696   0.2438
   1.250   0.7066   0.00633   0.00129  -0.1247   0.7623   0.2604
   1.500   0.7349   0.00625   0.00133  -0.1248   0.7538   0.2969
   1.750   0.7575   0.00485   0.00147  -0.1240   0.7455   1.0000
   2.000   0.7852   0.00492   0.00149  -0.1239   0.7303   1.0000
   2.250   0.8119   0.00506   0.00149  -0.1235   0.6960   1.0000
   2.500   0.8371   0.00538   0.00158  -0.1230   0.6317   1.0000
   2.750   0.8598   0.00609   0.00183  -0.1221   0.5338   1.0000
   3.000   0.8842   0.00664   0.00207  -0.1216   0.4655   1.0000
   3.250   0.9083   0.00721   0.00232  -0.1210   0.3957   1.0000
   3.500   0.9329   0.00772   0.00259  -0.1206   0.3424   1.0000
   3.750   0.9582   0.00813   0.00283  -0.1202   0.3034   1.0000
   4.000   0.9830   0.00858   0.00308  -0.1198   0.2572   1.0000
   4.250   1.0063   0.00922   0.00341  -0.1192   0.1948   1.0000
   4.500   1.0266   0.01027   0.00398  -0.1182   0.0993   1.0000
   4.750   1.0489   0.01105   0.00449  -0.1173   0.0499   1.0000
   5.000   1.0737   0.01149   0.00489  -0.1168   0.0385   1.0000
   5.250   1.0992   0.01180   0.00520  -0.1164   0.0344   1.0000
   5.500   1.1233   0.01232   0.00573  -0.1157   0.0289   1.0000
   5.750   1.1481   0.01270   0.00617  -0.1152   0.0273   1.0000
   6.000   1.1733   0.01302   0.00653  -0.1148   0.0260   1.0000
   6.250   1.1978   0.01340   0.00696  -0.1143   0.0242   1.0000
   6.500   1.2218   0.01385   0.00744  -0.1136   0.0226   1.0000
   6.750   1.2448   0.01442   0.00806  -0.1128   0.0211   1.0000
   7.000   1.2622   0.01569   0.00947  -0.1109   0.0185   1.0000
   7.250   1.2903   0.01550   0.00924  -0.1112   0.0178   1.0000
   7.500   1.3153   0.01570   0.00948  -0.1108   0.0168   1.0000
   7.750   1.3394   0.01601   0.00981  -0.1103   0.0155   1.0000
   8.000   1.3632   0.01633   0.01014  -0.1098   0.0143   1.0000
   8.250   1.3852   0.01686   0.01068  -0.1089   0.0127   1.0000
   8.500   1.4046   0.01767   0.01158  -0.1076   0.0114   1.0000
   8.750   1.4311   0.01760   0.01149  -0.1076   0.0105   1.0000
   9.000   1.4553   0.01778   0.01155  -0.1073   0.0069   1.0000
   9.250   1.4741   0.01859   0.01235  -0.1059   0.0037   1.0000
   9.500   1.4923   0.01942   0.01327  -0.1044   0.0029   1.0000
   9.750   1.5074   0.02059   0.01457  -0.1024   0.0023   1.0000
  10.000   1.5235   0.02157   0.01567  -0.1005   0.0021   1.0000
  10.250   1.5393   0.02250   0.01672  -0.0987   0.0021   1.0000
  10.500   1.5533   0.02353   0.01787  -0.0966   0.0020   1.0000
  10.750   1.5653   0.02463   0.01911  -0.0942   0.0019   1.0000
  11.000   1.5746   0.02576   0.02038  -0.0913   0.0018   1.0000
  11.250   1.5817   0.02694   0.02169  -0.0881   0.0018   1.0000
  11.500   1.5877   0.02826   0.02316  -0.0850   0.0017   1.0000
  11.750   1.5926   0.02971   0.02476  -0.0819   0.0017   1.0000
  12.000   1.5970   0.03125   0.02644  -0.0790   0.0016   1.0000
  12.250   1.6003   0.03291   0.02827  -0.0762   0.0015   1.0000
  12.500   1.6020   0.03478   0.03030  -0.0734   0.0015   1.0000
  12.750   1.6025   0.03681   0.03248  -0.0709   0.0015   1.0000
  13.000   1.6017   0.03905   0.03488  -0.0684   0.0014   1.0000
  13.250   1.6002   0.04143   0.03741  -0.0663   0.0014   1.0000
  13.500   1.5954   0.04426   0.04041  -0.0642   0.0013   1.0000
  13.750   1.5873   0.04759   0.04392  -0.0624   0.0013   1.0000
  14.000   1.5781   0.05122   0.04774  -0.0610   0.0013   1.0000
  14.250   1.5655   0.05545   0.05215  -0.0601   0.0013   1.0000
  14.500   1.5504   0.06032   0.05720  -0.0598   0.0012   1.0000
  14.750   1.5339   0.06575   0.06282  -0.0603   0.0012   1.0000
  15.000   1.5160   0.07197   0.06922  -0.0618   0.0012   1.0000
  15.250   1.4948   0.07949   0.07692  -0.0646   0.0012   1.0000
  15.500   1.4771   0.08697   0.08457  -0.0680   0.0012   1.0000
  15.750   1.4553   0.09589   0.09367  -0.0726   0.0012   1.0000
  16.000   1.4328   0.10547   0.10340  -0.0777   0.0012   1.0000
  16.250   1.4080   0.11580   0.11388  -0.0832   0.0013   1.0000
  16.500   1.3791   0.12733   0.12556  -0.0893   0.0013   1.0000
  16.750   1.3440   0.14091   0.13930  -0.0966   0.0014   1.0000
  17.000   1.2954   0.15912   0.15769  -0.1065   0.0015   1.0000
  17.250   1.1404   0.22658   0.22525  -0.1425   0.0023   1.0000
  17.500   1.1428   0.23350   0.23216  -0.1460   0.0023   1.0000
  17.750   1.1464   0.23984   0.23849  -0.1494   0.0023   1.0000
  18.000   1.1502   0.24636   0.24499  -0.1529   0.0023   1.0000
  18.250   0.8285   0.21562   0.21436  -0.1039   0.0034   1.0000
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