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HAM-STD HS1-708 AIRFOIL (hs1708-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-708 AIRFOIL (hs1708-il)
Reynolds number: 50,000
Max Cl/Cd: 43 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1708-il-50000-n5.txt
Download as CSV file: xf-hs1708-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3608   0.11057   0.10407  -0.0269   1.0000   0.0915
  -7.750  -0.3746   0.10955   0.10315  -0.0245   1.0000   0.0922
  -7.500  -0.3859   0.10815   0.10184  -0.0227   1.0000   0.0925
  -6.500  -0.4012   0.09268   0.08650  -0.0299   1.0000   0.0549
  -6.250  -0.3969   0.08940   0.08324  -0.0301   1.0000   0.0545
  -5.750  -0.3646   0.08247   0.07629  -0.0346   0.9943   0.0589
  -5.500  -0.3408   0.07771   0.07146  -0.0408   0.9904   0.0598
  -5.250  -0.3108   0.07202   0.06564  -0.0488   0.9867   0.0596
  -5.000  -0.2780   0.06657   0.06002  -0.0566   0.9834   0.0610
  -4.750  -0.2369   0.06004   0.05319  -0.0668   0.9801   0.0654
  -4.500  -0.1949   0.05393   0.04670  -0.0755   0.9774   0.0694
  -4.250  -0.1594   0.05079   0.04330  -0.0801   0.9747   0.0760
  -4.000  -0.1086   0.04466   0.03649  -0.0892   0.9732   0.0828
  -3.750  -0.0727   0.04214   0.03361  -0.0927   0.9706   0.0889
  -3.500  -0.0313   0.03874   0.02956  -0.0975   0.9684   0.0969
  -3.250   0.0045   0.03699   0.02737  -0.1002   0.9656   0.1044
  -3.000   0.0421   0.03536   0.02530  -0.1030   0.9630   0.1127
  -2.750   0.0818   0.03384   0.02321  -0.1061   0.9606   0.1231
  -2.500   0.1159   0.03319   0.02241  -0.1078   0.9575   0.1313
  -2.250   0.1460   0.03266   0.02163  -0.1088   0.9529   0.1427
  -2.000   0.1817   0.03190   0.02051  -0.1107   0.9491   0.1533
  -1.750   0.2180   0.03158   0.02002  -0.1127   0.9456   0.1682
  -1.500   0.2484   0.03129   0.01955  -0.1135   0.9407   0.1821
  -1.250   0.2800   0.03109   0.01918  -0.1145   0.9357   0.1973
  -1.000   0.3160   0.03093   0.01893  -0.1163   0.9317   0.2162
  -0.750   0.3457   0.03082   0.01873  -0.1170   0.9262   0.2343
  -0.500   0.3772   0.03073   0.01856  -0.1179   0.9207   0.2554
  -0.250   0.4141   0.03058   0.01842  -0.1199   0.9166   0.2799
   0.000   0.4403   0.03056   0.01847  -0.1200   0.9097   0.3025
   0.250   0.4748   0.03043   0.01844  -0.1216   0.9044   0.3334
   0.500   0.5083   0.03024   0.01852  -0.1230   0.8987   0.3793
   0.750   0.5278   0.02887   0.01859  -0.1212   0.8906   1.0000
   1.000   0.5602   0.02916   0.01861  -0.1220   0.8818   1.0000
   1.250   0.6006   0.02918   0.01842  -0.1239   0.8729   1.0000
   1.500   0.6307   0.02928   0.01839  -0.1240   0.8605   1.0000
   1.750   0.6617   0.02936   0.01839  -0.1242   0.8488   1.0000
   2.000   0.6960   0.02937   0.01834  -0.1250   0.8392   1.0000
   2.250   0.7308   0.02936   0.01831  -0.1258   0.8301   1.0000
   2.500   0.7572   0.02955   0.01852  -0.1253   0.8185   1.0000
   2.750   0.7860   0.02965   0.01864  -0.1251   0.8074   1.0000
   3.000   0.8208   0.02949   0.01851  -0.1257   0.7980   1.0000
   3.250   0.8505   0.02942   0.01854  -0.1254   0.7864   1.0000
   3.500   0.8764   0.02944   0.01864  -0.1245   0.7728   1.0000
   3.750   0.9027   0.02940   0.01869  -0.1236   0.7587   1.0000
   4.000   0.9295   0.02927   0.01867  -0.1227   0.7440   1.0000
   4.500   0.9829   0.02883   0.01850  -0.1205   0.7119   1.0000
   4.750   1.0005   0.02899   0.01880  -0.1183   0.6898   1.0000
   5.000   1.0273   0.02868   0.01865  -0.1170   0.6704   1.0000
   5.250   1.0488   0.02865   0.01876  -0.1152   0.6461   1.0000
   5.500   1.0773   0.02828   0.01850  -0.1141   0.6221   1.0000
   5.750   1.1097   0.02776   0.01808  -0.1134   0.5963   1.0000
   6.000   1.1420   0.02741   0.01774  -0.1128   0.5679   1.0000
   6.250   1.1713   0.02743   0.01771  -0.1120   0.5378   1.0000
   6.500   1.1959   0.02781   0.01807  -0.1107   0.5062   1.0000
   6.750   1.2142   0.02843   0.01857  -0.1085   0.4688   1.0000
   7.000   1.2268   0.02927   0.01924  -0.1056   0.4287   1.0000
   7.250   1.2371   0.03025   0.02001  -0.1026   0.3907   1.0000
   7.500   1.2474   0.03131   0.02100  -0.0998   0.3582   1.0000
   7.750   1.2565   0.03242   0.02210  -0.0970   0.3286   1.0000
   8.000   1.2636   0.03362   0.02330  -0.0939   0.2985   1.0000
   8.250   1.2697   0.03495   0.02465  -0.0910   0.2659   1.0000
   8.500   1.2736   0.03651   0.02613  -0.0880   0.2296   1.0000
   8.750   1.2761   0.03837   0.02782  -0.0852   0.1904   1.0000
   9.000   1.2784   0.04049   0.02972  -0.0826   0.1590   1.0000
   9.250   1.2830   0.04266   0.03179  -0.0802   0.1374   1.0000
   9.500   1.2883   0.04486   0.03395  -0.0780   0.1227   1.0000
   9.750   1.2947   0.04699   0.03609  -0.0760   0.1110   1.0000
  10.000   1.3016   0.04912   0.03826  -0.0741   0.1020   1.0000
  10.250   1.3097   0.05121   0.04040  -0.0723   0.0955   1.0000
  10.500   1.3226   0.05318   0.04252  -0.0705   0.0903   1.0000
  10.750   1.3351   0.05517   0.04467  -0.0689   0.0852   1.0000
  11.000   1.3468   0.05728   0.04676  -0.0674   0.0806   1.0000
  11.250   1.3571   0.05956   0.04940  -0.0659   0.0758   1.0000
  11.500   1.3692   0.06184   0.05190  -0.0645   0.0722   1.0000
  11.750   1.3892   0.06411   0.05417  -0.0635   0.0693   1.0000
  12.000   1.3965   0.06717   0.05763  -0.0620   0.0671   1.0000
  12.250   1.3957   0.07054   0.06140  -0.0603   0.0648   1.0000
  12.500   1.3917   0.07405   0.06523  -0.0589   0.0626   1.0000
  12.750   1.3873   0.07759   0.06902  -0.0577   0.0606   1.0000
  13.000   1.3837   0.08120   0.07283  -0.0568   0.0590   1.0000
  13.250   1.3803   0.08515   0.07697  -0.0560   0.0579   1.0000
  13.750   1.3600   0.09480   0.08707  -0.0556   0.0566   1.0000
  14.000   1.3389   0.10078   0.09337  -0.0566   0.0565   1.0000
  14.250   1.3162   0.10742   0.10029  -0.0587   0.0564   1.0000
  14.500   1.2924   0.11482   0.10793  -0.0620   0.0565   1.0000
  14.750   1.2678   0.12316   0.11648  -0.0665   0.0566   1.0000
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