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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 500,000
Max Cl/Cd: 123.58 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq358-il-500000.txt
Download as CSV file: xf-hq358-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3433   0.09366   0.09149  -0.0324   1.0000   0.0096
  -8.000  -0.3506   0.09191   0.08980  -0.0308   1.0000   0.0097
  -7.750  -0.3623   0.09049   0.08842  -0.0277   1.0000   0.0096
  -7.500  -0.3502   0.08697   0.08492  -0.0319   0.9976   0.0099
  -7.250  -0.3309   0.08253   0.08048  -0.0384   0.9938   0.0100
  -7.000  -0.3090   0.07741   0.07537  -0.0461   0.9884   0.0100
  -6.750  -0.2815   0.07171   0.06966  -0.0559   0.9846   0.0101
  -6.500  -0.2481   0.06513   0.06303  -0.0682   0.9821   0.0101
  -6.250  -0.2220   0.05936   0.05719  -0.0766   0.9758   0.0101
  -6.000  -0.1973   0.04944   0.04713  -0.0886   0.9717   0.0109
  -5.750  -0.1668   0.04539   0.04298  -0.0945   0.9700   0.0117
  -5.500  -0.1368   0.04145   0.03890  -0.0993   0.9662   0.0127
  -5.250  -0.1063   0.03741   0.03466  -0.1032   0.9612   0.0150
  -5.000  -0.0647   0.03549   0.03245  -0.1055   0.9583   0.0178
  -3.000   0.1550   0.01282   0.00742  -0.1103   0.9169   0.0159
  -2.750   0.1816   0.01113   0.00552  -0.1095   0.9110   0.0142
  -2.500   0.2086   0.01003   0.00428  -0.1090   0.9051   0.0138
  -2.250   0.2359   0.00932   0.00346  -0.1086   0.8996   0.0148
  -2.000   0.2630   0.00886   0.00288  -0.1082   0.8920   0.0171
  -1.750   0.2899   0.00846   0.00240  -0.1078   0.8834   0.0238
  -1.500   0.3173   0.00799   0.00203  -0.1075   0.8749   0.0876
  -1.250   0.3424   0.00681   0.00187  -0.1077   0.8655   0.4460
  -1.000   0.3677   0.00638   0.00192  -0.1072   0.8574   0.6277
  -0.750   0.3929   0.00623   0.00194  -0.1064   0.8494   0.7139
  -0.500   0.4188   0.00617   0.00193  -0.1057   0.8405   0.7525
  -0.250   0.4449   0.00611   0.00188  -0.1051   0.8318   0.7812
   0.000   0.4696   0.00602   0.00185  -0.1041   0.8222   0.8201
   0.250   0.4940   0.00590   0.00180  -0.1032   0.8124   0.8535
   0.500   0.5189   0.00579   0.00174  -0.1023   0.8035   0.8835
   0.750   0.5525   0.00561   0.00163  -0.1033   0.7944   1.0000
   1.000   0.5806   0.00566   0.00162  -0.1034   0.7837   1.0000
   1.250   0.6085   0.00572   0.00163  -0.1035   0.7729   1.0000
   1.500   0.6360   0.00579   0.00164  -0.1034   0.7612   1.0000
   1.750   0.6634   0.00586   0.00165  -0.1033   0.7487   1.0000
   2.000   0.6906   0.00595   0.00169  -0.1031   0.7353   1.0000
   2.250   0.7175   0.00605   0.00173  -0.1029   0.7200   1.0000
   2.500   0.7442   0.00616   0.00181  -0.1027   0.7034   1.0000
   2.750   0.7705   0.00629   0.00188  -0.1023   0.6845   1.0000
   3.000   0.7965   0.00645   0.00196  -0.1019   0.6616   1.0000
   3.250   0.8218   0.00665   0.00206  -0.1014   0.6334   1.0000
   3.500   0.8466   0.00689   0.00218  -0.1008   0.5981   1.0000
   3.750   0.8704   0.00722   0.00234  -0.1000   0.5549   1.0000
   4.000   0.8931   0.00765   0.00259  -0.0991   0.5033   1.0000
   4.250   0.9151   0.00818   0.00287  -0.0982   0.4467   1.0000
   4.500   0.9370   0.00876   0.00319  -0.0973   0.3911   1.0000
   4.750   0.9596   0.00929   0.00352  -0.0965   0.3446   1.0000
   5.000   0.9811   0.00994   0.00388  -0.0956   0.2911   1.0000
   5.250   1.0042   0.01043   0.00426  -0.0950   0.2593   1.0000
   5.500   1.0281   0.01085   0.00460  -0.0945   0.2346   1.0000
   5.750   1.0510   0.01136   0.00494  -0.0938   0.1969   1.0000
   6.000   1.0707   0.01224   0.00542  -0.0928   0.1281   1.0000
   6.250   1.0845   0.01384   0.00642  -0.0909   0.0357   1.0000
   6.500   1.1029   0.01503   0.00750  -0.0892   0.0082   1.0000
   6.750   1.1251   0.01570   0.00830  -0.0882   0.0073   1.0000
   7.000   1.1462   0.01648   0.00926  -0.0870   0.0068   1.0000
   7.250   1.1657   0.01743   0.01035  -0.0856   0.0067   1.0000
   7.500   1.1834   0.01854   0.01161  -0.0838   0.0066   1.0000
   7.750   1.1991   0.01985   0.01308  -0.0818   0.0066   1.0000
   8.000   1.2132   0.02139   0.01477  -0.0795   0.0067   1.0000
   8.250   1.2269   0.02316   0.01671  -0.0772   0.0069   1.0000
   8.500   1.2413   0.02533   0.01906  -0.0751   0.0072   1.0000
   8.750   1.2579   0.02729   0.02120  -0.0734   0.0071   1.0000
   9.000   1.2745   0.02890   0.02297  -0.0719   0.0067   1.0000
   9.250   1.2896   0.03047   0.02468  -0.0702   0.0062   1.0000
   9.500   1.3026   0.03353   0.02804  -0.0682   0.0064   1.0000
   9.750   1.3108   0.03697   0.03183  -0.0656   0.0066   1.0000
  10.000   1.3105   0.04130   0.03660  -0.0621   0.0070   1.0000
  10.250   1.2978   0.04583   0.04151  -0.0574   0.0076   1.0000
  10.750   1.1940   0.04612   0.04251  -0.0443   0.0078   1.0000
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