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HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HUGHES HELICOPTERS HH-02 AIRFOIL (hh02-il)
Reynolds number: 50,000
Max Cl/Cd: 30.54 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hh02-il-50000.txt
Download as CSV file: xf-hh02-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HUGHES HELICOPTERS HH-02 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.5049   0.09640   0.09105   0.0249   1.0000   0.3138
  -7.250  -0.4937   0.09278   0.08745   0.0242   1.0000   0.3320
  -7.000  -0.4976   0.09045   0.08519   0.0219   1.0000   0.3533
  -6.750  -0.4750   0.08586   0.08059   0.0227   1.0000   0.3735
  -6.500  -0.4731   0.08334   0.07813   0.0220   1.0000   0.4008
  -6.250  -0.4616   0.08031   0.07511   0.0227   1.0000   0.4309
  -6.000  -0.4332   0.07583   0.07059   0.0236   1.0000   0.4553
  -5.750  -0.4644   0.05980   0.05420  -0.0210   1.0000   0.2356
  -5.500  -0.4551   0.04862   0.04193  -0.0312   1.0000   0.1505
  -5.250  -0.4456   0.04437   0.03692  -0.0313   1.0000   0.1394
  -5.000  -0.4327   0.04126   0.03352  -0.0303   1.0000   0.1378
  -4.750  -0.4177   0.03825   0.03011  -0.0293   1.0000   0.1353
  -4.500  -0.4000   0.03536   0.02671  -0.0283   1.0000   0.1324
  -4.250  -0.3803   0.03291   0.02379  -0.0273   1.0000   0.1321
  -4.000  -0.3596   0.03105   0.02149  -0.0264   1.0000   0.1371
  -3.750  -0.3370   0.02927   0.01921  -0.0255   1.0000   0.1417
  -3.500  -0.3138   0.02750   0.01737  -0.0248   1.0000   0.1475
  -3.250  -0.2900   0.02613   0.01581  -0.0242   1.0000   0.1591
  -3.000  -0.2650   0.02484   0.01447  -0.0236   1.0000   0.1744
  -2.750  -0.2393   0.02366   0.01327  -0.0232   1.0000   0.2003
  -2.500  -0.2103   0.02200   0.01203  -0.0235   1.0000   0.2637
  -2.250  -0.2028   0.01937   0.01194  -0.0167   1.0000   0.7257
  -2.000  -0.1441   0.01870   0.01146  -0.0205   1.0000   1.0000
  -1.750  -0.1263   0.01887   0.01118  -0.0203   1.0000   1.0000
  -1.500  -0.1069   0.01912   0.01104  -0.0203   1.0000   1.0000
  -1.250  -0.0868   0.01942   0.01101  -0.0203   1.0000   1.0000
  -1.000  -0.0665   0.01978   0.01106  -0.0203   1.0000   1.0000
  -0.750  -0.0460   0.02018   0.01119  -0.0203   1.0000   1.0000
  -0.500  -0.0256   0.02063   0.01137  -0.0203   1.0000   1.0000
  -0.250  -0.0053   0.02111   0.01165  -0.0203   1.0000   1.0000
   0.000   0.0357   0.02188   0.01218  -0.0243   0.9926   1.0000
   0.250   0.0847   0.02282   0.01290  -0.0296   0.9819   1.0000
   0.500   0.1326   0.02381   0.01373  -0.0347   0.9698   1.0000
   0.750   0.1788   0.02486   0.01465  -0.0394   0.9562   1.0000
   1.000   0.2263   0.02603   0.01573  -0.0441   0.9412   1.0000
   1.250   0.2726   0.02729   0.01694  -0.0484   0.9248   1.0000
   1.500   0.3088   0.02850   0.01813  -0.0508   0.9068   1.0000
   1.750   0.3467   0.02977   0.01940  -0.0532   0.8879   1.0000
   2.000   0.3816   0.03094   0.02060  -0.0549   0.8686   1.0000
   2.250   0.4143   0.03198   0.02168  -0.0559   0.8489   1.0000
   2.500   0.4420   0.03290   0.02263  -0.0560   0.8285   1.0000
   2.750   0.4731   0.03371   0.02351  -0.0562   0.8076   1.0000
   3.000   0.5041   0.03442   0.02430  -0.0558   0.7867   1.0000
   3.250   0.5293   0.03499   0.02495  -0.0547   0.7640   1.0000
   3.500   0.5594   0.03529   0.02533  -0.0534   0.7434   1.0000
   3.750   0.5820   0.03561   0.02574  -0.0516   0.7192   1.0000
   4.000   0.6116   0.03526   0.02552  -0.0489   0.6998   1.0000
   4.250   0.6332   0.03531   0.02566  -0.0466   0.6745   1.0000
   4.500   0.6602   0.03438   0.02483  -0.0428   0.6559   1.0000
   4.750   0.6825   0.03403   0.02459  -0.0400   0.6310   1.0000
   5.000   0.7080   0.03273   0.02340  -0.0355   0.6123   1.0000
   5.250   0.7310   0.03203   0.02280  -0.0322   0.5881   1.0000
   5.500   0.7552   0.03062   0.02143  -0.0275   0.5677   1.0000
   5.750   0.7782   0.02989   0.02077  -0.0240   0.5415   1.0000
   6.000   0.8013   0.02904   0.01991  -0.0201   0.5158   1.0000
   6.250   0.8242   0.02838   0.01918  -0.0165   0.4884   1.0000
   6.500   0.8473   0.02831   0.01904  -0.0138   0.4579   1.0000
   6.750   0.8704   0.02863   0.01931  -0.0118   0.4263   1.0000
   7.000   0.8935   0.02926   0.01984  -0.0101   0.3954   1.0000
   7.250   0.9166   0.03020   0.02069  -0.0087   0.3658   1.0000
   7.500   0.9394   0.03137   0.02176  -0.0074   0.3371   1.0000
   7.750   0.9624   0.03265   0.02288  -0.0061   0.3108   1.0000
   8.000   0.9843   0.03447   0.02486  -0.0057   0.2843   1.0000
   8.250   1.0057   0.03637   0.02683  -0.0052   0.2607   1.0000
   8.500   1.0270   0.03846   0.02903  -0.0046   0.2403   1.0000
   8.750   1.0490   0.04030   0.03075  -0.0036   0.2213   1.0000
   9.000   1.0669   0.04298   0.03377  -0.0034   0.2048   1.0000
   9.250   1.0837   0.04566   0.03667  -0.0030   0.1897   1.0000
   9.500   1.1015   0.04836   0.03948  -0.0024   0.1768   1.0000
   9.750   1.1062   0.05258   0.04433  -0.0026   0.1676   1.0000
  10.000   1.1118   0.05641   0.04844  -0.0024   0.1587   1.0000
  10.250   1.1095   0.06102   0.05344  -0.0025   0.1533   1.0000
  10.500   1.1144   0.06500   0.05754  -0.0020   0.1470   1.0000
  10.750   1.0921   0.07108   0.06398  -0.0032   0.1466   1.0000
  11.000   1.0657   0.07728   0.07036  -0.0048   0.1474   1.0000
  11.250   1.0396   0.08388   0.07704  -0.0067   0.1483   1.0000
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