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HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.4 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1606-il-1000000-n5.txt
Download as CSV file: xf-hs1606-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2525   0.09518   0.09359  -0.0411   0.9840   0.0052
  -9.500  -0.2461   0.09121   0.08962  -0.0428   0.9766   0.0053
  -7.000  -0.2691   0.06738   0.06547  -0.0597   0.8873   0.0028
  -6.750  -0.2491   0.06182   0.05985  -0.0672   0.8777   0.0027
  -6.500  -0.2235   0.05512   0.05308  -0.0767   0.8701   0.0026
  -6.000  -0.1286   0.01515   0.01116  -0.1176   0.8583   0.0023
  -5.750  -0.0991   0.01332   0.00895  -0.1185   0.8538   0.0024
  -5.500  -0.0700   0.01213   0.00747  -0.1190   0.8495   0.0026
  -5.250  -0.0411   0.01138   0.00652  -0.1194   0.8455   0.0028
  -5.000  -0.0123   0.01091   0.00593  -0.1197   0.8415   0.0029
  -4.750   0.0170   0.00995   0.00477  -0.1202   0.8379   0.0033
  -4.250   0.0748   0.00906   0.00369  -0.1207   0.8315   0.0039
  -4.000   0.1037   0.00871   0.00326  -0.1210   0.8280   0.0041
  -3.750   0.1326   0.00841   0.00288  -0.1212   0.8246   0.0044
  -3.500   0.1613   0.00820   0.00262  -0.1214   0.8213   0.0049
  -3.250   0.1901   0.00797   0.00234  -0.1215   0.8175   0.0052
  -3.000   0.2190   0.00774   0.00203  -0.1217   0.8123   0.0053
  -2.750   0.2475   0.00758   0.00177  -0.1217   0.8061   0.0054
  -2.500   0.2763   0.00742   0.00155  -0.1218   0.7993   0.0057
  -2.000   0.3338   0.00695   0.00118  -0.1222   0.7869   0.0548
  -1.750   0.3622   0.00682   0.00110  -0.1224   0.7805   0.0765
  -1.500   0.3908   0.00673   0.00104  -0.1225   0.7746   0.0959
  -1.250   0.4193   0.00663   0.00102  -0.1227   0.7674   0.1254
  -1.000   0.4478   0.00660   0.00100  -0.1228   0.7615   0.1360
  -0.750   0.4763   0.00656   0.00098  -0.1229   0.7558   0.1471
  -0.500   0.5047   0.00655   0.00097  -0.1230   0.7503   0.1561
  -0.250   0.5332   0.00654   0.00097  -0.1231   0.7436   0.1629
   0.000   0.5615   0.00654   0.00097  -0.1232   0.7365   0.1700
   0.250   0.5898   0.00653   0.00097  -0.1233   0.7280   0.1775
   0.500   0.6180   0.00654   0.00099  -0.1233   0.7184   0.1866
   0.750   0.6461   0.00656   0.00101  -0.1233   0.7052   0.1953
   1.000   0.6737   0.00663   0.00104  -0.1233   0.6841   0.2046
   1.250   0.7007   0.00676   0.00109  -0.1231   0.6495   0.2133
   1.500   0.7266   0.00705   0.00119  -0.1228   0.5957   0.2222
   1.750   0.7527   0.00735   0.00133  -0.1225   0.5503   0.2314
   2.000   0.7783   0.00771   0.00150  -0.1222   0.4979   0.2444
   2.500   0.8269   0.00877   0.00201  -0.1214   0.3439   0.2942
   3.000   0.8737   0.00806   0.00249  -0.1201   0.2778   1.0000
   3.250   0.8996   0.00839   0.00267  -0.1199   0.2440   1.0000
   3.500   0.9241   0.00891   0.00295  -0.1194   0.1922   1.0000
   3.750   0.9480   0.00950   0.00327  -0.1189   0.1374   1.0000
   4.000   0.9706   0.01027   0.00371  -0.1182   0.0704   1.0000
   4.250   0.9958   0.01067   0.00401  -0.1178   0.0494   1.0000
   4.500   1.0215   0.01099   0.00427  -0.1174   0.0395   1.0000
   4.750   1.0474   0.01125   0.00454  -0.1172   0.0348   1.0000
   5.000   1.0729   0.01156   0.00483  -0.1168   0.0294   1.0000
   5.250   1.0987   0.01183   0.00511  -0.1165   0.0267   1.0000
   5.500   1.1242   0.01211   0.00540  -0.1161   0.0245   1.0000
   5.750   1.1494   0.01244   0.00572  -0.1157   0.0222   1.0000
   6.000   1.1742   0.01281   0.00613  -0.1152   0.0197   1.0000
   6.250   1.1988   0.01319   0.00655  -0.1147   0.0183   1.0000
   6.500   1.2237   0.01350   0.00690  -0.1143   0.0179   1.0000
   6.750   1.2483   0.01384   0.00728  -0.1138   0.0171   1.0000
   7.000   1.2728   0.01416   0.00762  -0.1133   0.0157   1.0000
   7.250   1.2968   0.01452   0.00795  -0.1128   0.0135   1.0000
   7.500   1.3198   0.01503   0.00850  -0.1120   0.0115   1.0000
   7.750   1.3437   0.01536   0.00888  -0.1115   0.0111   1.0000
   8.000   1.3673   0.01573   0.00929  -0.1109   0.0103   1.0000
   8.250   1.3903   0.01614   0.00972  -0.1102   0.0090   1.0000
   8.500   1.4126   0.01662   0.01018  -0.1094   0.0073   1.0000
   8.750   1.4345   0.01711   0.01072  -0.1086   0.0059   1.0000
   9.000   1.4545   0.01779   0.01138  -0.1074   0.0034   1.0000
   9.250   1.4735   0.01856   0.01220  -0.1061   0.0021   1.0000
   9.500   1.4927   0.01928   0.01302  -0.1048   0.0017   1.0000
   9.750   1.5105   0.02010   0.01393  -0.1032   0.0014   1.0000
  10.000   1.5270   0.02104   0.01498  -0.1015   0.0011   1.0000
  10.250   1.5446   0.02179   0.01581  -0.1000   0.0010   1.0000
  10.500   1.5612   0.02257   0.01669  -0.0983   0.0009   1.0000
  10.750   1.5763   0.02342   0.01764  -0.0964   0.0009   1.0000
  11.000   1.5898   0.02432   0.01865  -0.0943   0.0008   1.0000
  11.250   1.6008   0.02525   0.01969  -0.0917   0.0008   1.0000
  11.500   1.6099   0.02627   0.02082  -0.0889   0.0008   1.0000
  11.750   1.6184   0.02738   0.02205  -0.0861   0.0007   1.0000
  12.000   1.6263   0.02855   0.02337  -0.0835   0.0007   1.0000
  12.250   1.6331   0.02986   0.02480  -0.0808   0.0007   1.0000
  12.500   1.6387   0.03129   0.02637  -0.0782   0.0007   1.0000
  12.750   1.6435   0.03283   0.02805  -0.0756   0.0006   1.0000
  13.000   1.6470   0.03453   0.02989  -0.0732   0.0006   1.0000
  13.250   1.6501   0.03633   0.03182  -0.0709   0.0006   1.0000
  13.500   1.6512   0.03836   0.03399  -0.0686   0.0006   1.0000
  13.750   1.6502   0.04068   0.03647  -0.0665   0.0006   1.0000
  14.000   1.6484   0.04316   0.03910  -0.0645   0.0005   1.0000
  14.250   1.6446   0.04594   0.04204  -0.0628   0.0005   1.0000
  14.500   1.6397   0.04897   0.04522  -0.0614   0.0005   1.0000
  14.750   1.6321   0.05242   0.04883  -0.0602   0.0005   1.0000
  15.000   1.6227   0.05629   0.05287  -0.0594   0.0005   1.0000
  15.250   1.6117   0.06059   0.05732  -0.0591   0.0005   1.0000
  15.500   1.5977   0.06558   0.06248  -0.0595   0.0005   1.0000
  15.750   1.5827   0.07120   0.06828  -0.0606   0.0005   1.0000
  16.000   1.5650   0.07779   0.07504  -0.0628   0.0005   1.0000
  16.250   1.5448   0.08537   0.08279  -0.0660   0.0005   1.0000
  16.500   1.5209   0.09426   0.09186  -0.0703   0.0005   1.0000
  16.750   1.4938   0.10441   0.10218  -0.0756   0.0005   1.0000
  17.000   1.4609   0.11621   0.11417  -0.0820   0.0005   1.0000
  17.250   1.4237   0.12948   0.12762  -0.0892   0.0005   1.0000
  17.500   1.3722   0.14707   0.14540  -0.0990   0.0006   1.0000
  17.750   1.2454   0.19029   0.18888  -0.1233   0.0007   1.0000
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