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HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il)
Reynolds number: 1,000,000
Max Cl/Cd: 168.96 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1708-il-1000000.txt
Download as CSV file: xf-hs1708-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2598   0.09307   0.09141  -0.0596   0.9770   0.0150
  -9.000  -0.2499   0.08905   0.08738  -0.0628   0.9633   0.0150
  -8.750  -0.3450   0.02351   0.02053  -0.1297   0.9036   0.0081
  -8.500  -0.3188   0.01938   0.01592  -0.1330   0.8970   0.0080
  -8.250  -0.2920   0.01720   0.01339  -0.1344   0.8910   0.0080
  -8.000  -0.2646   0.01566   0.01157  -0.1353   0.8859   0.0080
  -7.750  -0.2364   0.01443   0.01010  -0.1360   0.8811   0.0080
  -7.500  -0.2082   0.01347   0.00894  -0.1365   0.8765   0.0081
  -7.250  -0.1798   0.01269   0.00797  -0.1369   0.8723   0.0082
  -7.000  -0.1510   0.01200   0.00715  -0.1374   0.8684   0.0082
  -6.750  -0.1221   0.01144   0.00646  -0.1378   0.8645   0.0083
  -6.500  -0.0931   0.01077   0.00563  -0.1382   0.8609   0.0086
  -6.250  -0.0641   0.01019   0.00489  -0.1385   0.8576   0.0092
  -6.000  -0.0349   0.00975   0.00438  -0.1389   0.8546   0.0100
  -5.750  -0.0057   0.00942   0.00398  -0.1392   0.8516   0.0109
  -5.500   0.0235   0.00903   0.00355  -0.1395   0.8486   0.0136
  -5.250   0.0526   0.00867   0.00319  -0.1398   0.8457   0.0225
  -5.000   0.0815   0.00849   0.00300  -0.1400   0.8427   0.0296
  -4.750   0.1107   0.00835   0.00285  -0.1403   0.8402   0.0337
  -4.500   0.1398   0.00818   0.00269  -0.1406   0.8377   0.0390
  -4.250   0.1689   0.00807   0.00257  -0.1408   0.8352   0.0427
  -4.000   0.1979   0.00796   0.00243  -0.1410   0.8323   0.0468
  -3.750   0.2267   0.00788   0.00234  -0.1412   0.8289   0.0525
  -3.500   0.2557   0.00779   0.00225  -0.1414   0.8250   0.0573
  -3.250   0.2846   0.00765   0.00213  -0.1416   0.8205   0.0640
  -3.000   0.3133   0.00761   0.00204  -0.1416   0.8162   0.0675
  -2.750   0.3423   0.00749   0.00194  -0.1419   0.8123   0.0759
  -2.500   0.3713   0.00740   0.00185  -0.1420   0.8085   0.0827
  -2.250   0.4002   0.00731   0.00179  -0.1422   0.8046   0.0943
  -2.000   0.4290   0.00724   0.00174  -0.1424   0.8007   0.1075
  -1.750   0.4580   0.00716   0.00170  -0.1426   0.7970   0.1202
  -1.500   0.4870   0.00708   0.00166  -0.1428   0.7928   0.1319
  -1.250   0.5158   0.00704   0.00163  -0.1429   0.7885   0.1431
  -1.000   0.5445   0.00704   0.00161  -0.1431   0.7849   0.1524
  -0.750   0.5736   0.00699   0.00161  -0.1433   0.7814   0.1625
  -0.500   0.6024   0.00695   0.00160  -0.1434   0.7774   0.1709
  -0.250   0.6312   0.00694   0.00159  -0.1436   0.7733   0.1799
   0.000   0.6599   0.00692   0.00159  -0.1437   0.7687   0.1896
   0.250   0.6887   0.00689   0.00159  -0.1438   0.7638   0.1978
   0.500   0.7174   0.00687   0.00160  -0.1440   0.7591   0.2086
   0.750   0.7460   0.00686   0.00162  -0.1441   0.7545   0.2192
   1.000   0.7748   0.00682   0.00163  -0.1443   0.7484   0.2320
   1.250   0.8031   0.00681   0.00164  -0.1443   0.7417   0.2482
   1.500   0.8318   0.00675   0.00167  -0.1445   0.7336   0.2717
   1.750   0.8602   0.00664   0.00172  -0.1447   0.7243   0.3445
   2.000   0.8820   0.00539   0.00185  -0.1436   0.7137   1.0000
   2.250   0.9101   0.00545   0.00188  -0.1436   0.7002   1.0000
   2.500   0.9377   0.00555   0.00192  -0.1435   0.6820   1.0000
   2.750   0.9642   0.00574   0.00198  -0.1431   0.6486   1.0000
   3.000   0.9865   0.00630   0.00217  -0.1420   0.5738   1.0000
   3.250   1.0086   0.00696   0.00248  -0.1410   0.5047   1.0000
   3.500   1.0326   0.00743   0.00272  -0.1404   0.4553   1.0000
   3.750   1.0556   0.00799   0.00300  -0.1396   0.3999   1.0000
   4.250   1.1044   0.00880   0.00350  -0.1385   0.3364   1.0000
   4.500   1.1295   0.00912   0.00372  -0.1381   0.3162   1.0000
   4.750   1.1551   0.00939   0.00393  -0.1377   0.2998   1.0000
   5.000   1.1804   0.00967   0.00415  -0.1373   0.2828   1.0000
   5.250   1.2052   0.00998   0.00438  -0.1368   0.2634   1.0000
   5.500   1.2293   0.01035   0.00464  -0.1362   0.2402   1.0000
   5.750   1.2519   0.01084   0.00497  -0.1354   0.2080   1.0000
   6.000   1.2730   0.01145   0.00538  -0.1343   0.1705   1.0000
   6.250   1.2925   0.01219   0.00588  -0.1329   0.1286   1.0000
   6.500   1.3098   0.01312   0.00651  -0.1312   0.0823   1.0000
   6.750   1.3302   0.01374   0.00702  -0.1300   0.0623   1.0000
   7.000   1.3522   0.01421   0.00745  -0.1290   0.0530   1.0000
   7.250   1.3731   0.01475   0.00795  -0.1279   0.0453   1.0000
   7.500   1.3960   0.01509   0.00833  -0.1270   0.0429   1.0000
   7.750   1.4172   0.01555   0.00878  -0.1260   0.0395   1.0000
   8.000   1.4361   0.01621   0.00946  -0.1244   0.0350   1.0000
   8.250   1.4580   0.01653   0.00982  -0.1234   0.0341   1.0000
   8.500   1.4787   0.01693   0.01025  -0.1223   0.0327   1.0000
   8.750   1.4982   0.01739   0.01075  -0.1209   0.0311   1.0000
   9.000   1.5161   0.01794   0.01131  -0.1192   0.0293   1.0000
   9.250   1.5294   0.01873   0.01216  -0.1167   0.0270   1.0000
   9.500   1.5423   0.01943   0.01294  -0.1141   0.0260   1.0000
   9.750   1.5604   0.01982   0.01336  -0.1126   0.0253   1.0000
  10.000   1.5778   0.02026   0.01385  -0.1110   0.0243   1.0000
  10.250   1.5947   0.02075   0.01435  -0.1094   0.0230   1.0000
  10.500   1.6097   0.02139   0.01500  -0.1075   0.0217   1.0000
  10.750   1.6209   0.02230   0.01596  -0.1050   0.0202   1.0000
  11.000   1.6278   0.02355   0.01733  -0.1020   0.0191   1.0000
  11.250   1.6440   0.02413   0.01796  -0.1005   0.0187   1.0000
  11.500   1.6594   0.02479   0.01866  -0.0989   0.0182   1.0000
  11.750   1.6741   0.02551   0.01943  -0.0973   0.0175   1.0000
  12.000   1.6887   0.02624   0.02021  -0.0958   0.0167   1.0000
  12.250   1.7017   0.02710   0.02110  -0.0941   0.0158   1.0000
  12.500   1.7122   0.02818   0.02221  -0.0922   0.0149   1.0000
  12.750   1.7154   0.02989   0.02401  -0.0895   0.0138   1.0000
  13.000   1.7270   0.03092   0.02512  -0.0879   0.0134   1.0000
  13.250   1.7398   0.03187   0.02614  -0.0865   0.0130   1.0000
  13.500   1.7512   0.03295   0.02728  -0.0850   0.0124   1.0000
  13.750   1.7617   0.03414   0.02851  -0.0836   0.0117   1.0000
  14.000   1.7703   0.03549   0.02990  -0.0820   0.0109   1.0000
  14.250   1.7736   0.03736   0.03182  -0.0800   0.0099   1.0000
  14.500   1.7780   0.03916   0.03372  -0.0783   0.0093   1.0000
  14.750   1.7862   0.04064   0.03527  -0.0769   0.0088   1.0000
  15.000   1.7922   0.04235   0.03704  -0.0755   0.0081   1.0000
  15.250   1.7943   0.04446   0.03920  -0.0740   0.0074   1.0000
  15.500   1.7894   0.04739   0.04223  -0.0722   0.0065   1.0000
  15.750   1.7919   0.04964   0.04459  -0.0710   0.0062   1.0000
  16.000   1.7923   0.05221   0.04725  -0.0699   0.0057   1.0000
  16.250   1.7902   0.05511   0.05024  -0.0689   0.0053   1.0000
  16.500   1.7857   0.05844   0.05366  -0.0681   0.0050   1.0000
  16.750   1.7768   0.06249   0.05782  -0.0675   0.0046   1.0000
  17.000   1.7629   0.06745   0.06293  -0.0674   0.0043   1.0000
  17.250   1.7568   0.07152   0.06712  -0.0675   0.0042   1.0000
  17.500   1.7483   0.07608   0.07181  -0.0680   0.0041   1.0000
  17.750   1.7381   0.08108   0.07695  -0.0689   0.0040   1.0000
  18.000   1.7263   0.08650   0.08251  -0.0702   0.0039   1.0000
  18.250   1.7123   0.09243   0.08858  -0.0718   0.0038   1.0000
  18.500   1.6962   0.09880   0.09510  -0.0739   0.0038   1.0000
  18.750   1.6790   0.10554   0.10198  -0.0763   0.0037   1.0000
  19.000   1.6610   0.11259   0.10917  -0.0791   0.0037   1.0000
  19.250   1.6420   0.11998   0.11670  -0.0823   0.0036   1.0000
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