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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 500,000
Max Cl/Cd: 121.06 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq359-il-500000.txt
Download as CSV file: xf-hq359-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/9 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.4274   0.16601   0.16347  -0.0194   1.0000   0.0070
 -14.000  -0.4212   0.16274   0.16020  -0.0207   1.0000   0.0070
  -8.250  -0.3656   0.08966   0.08763  -0.0341   0.9994   0.0120
  -8.000  -0.3520   0.08513   0.08310  -0.0386   0.9969   0.0123
  -7.750  -0.3340   0.08252   0.08049  -0.0410   0.9947   0.0133
  -7.500  -0.3183   0.07866   0.07663  -0.0459   0.9903   0.0142
  -7.250  -0.3002   0.07392   0.07189  -0.0530   0.9852   0.0147
  -7.000  -0.2745   0.06796   0.06592  -0.0634   0.9812   0.0154
  -6.750  -0.2488   0.06146   0.05940  -0.0753   0.9747   0.0160
  -6.500  -0.2125   0.05390   0.05170  -0.0890   0.9713   0.0172
  -6.250  -0.1701   0.04864   0.04621  -0.0982   0.9692   0.0183
  -6.000  -0.1466   0.04454   0.04191  -0.1019   0.9619   0.0185
  -5.750  -0.1176   0.04014   0.03726  -0.1061   0.9577   0.0185
  -5.500  -0.1051   0.03258   0.02943  -0.1099   0.9496   0.0201
  -5.250  -0.0802   0.03026   0.02698  -0.1113   0.9446   0.0212
  -5.000  -0.0557   0.02797   0.02448  -0.1120   0.9390   0.0227
  -4.750  -0.0306   0.02563   0.02188  -0.1122   0.9326   0.0248
  -4.500   0.0017   0.02580   0.02174  -0.1116   0.9284   0.0282
  -4.250   0.0222   0.01733   0.01254  -0.1111   0.9206   0.0163
  -4.000   0.0495   0.01345   0.00806  -0.1103   0.9159   0.0138
  -3.750   0.0756   0.01232   0.00676  -0.1097   0.9099   0.0144
  -3.500   0.1025   0.01154   0.00587  -0.1093   0.9043   0.0155
  -3.250   0.1297   0.01107   0.00532  -0.1091   0.8993   0.0173
  -3.000   0.1559   0.01024   0.00436  -0.1086   0.8928   0.0175
  -2.750   0.1834   0.00963   0.00364  -0.1083   0.8877   0.0181
  -2.500   0.2102   0.00903   0.00292  -0.1080   0.8808   0.0216
  -2.250   0.2380   0.00861   0.00254  -0.1078   0.8748   0.0525
  -2.000   0.2647   0.00838   0.00237  -0.1076   0.8665   0.0822
  -1.750   0.2911   0.00766   0.00212  -0.1076   0.8585   0.2484
  -1.500   0.3153   0.00669   0.00208  -0.1074   0.8491   0.5671
  -1.250   0.3415   0.00656   0.00207  -0.1069   0.8406   0.6362
  -1.000   0.3686   0.00651   0.00202  -0.1065   0.8333   0.6695
  -0.750   0.3952   0.00648   0.00201  -0.1061   0.8247   0.6990
  -0.500   0.4217   0.00646   0.00200  -0.1055   0.8169   0.7335
  -0.250   0.4477   0.00643   0.00201  -0.1049   0.8079   0.7630
   0.000   0.4737   0.00640   0.00201  -0.1043   0.7988   0.7875
   0.250   0.5005   0.00638   0.00195  -0.1039   0.7898   0.8026
   0.500   0.5272   0.00635   0.00192  -0.1036   0.7798   0.8150
   0.750   0.5538   0.00632   0.00190  -0.1032   0.7700   0.8288
   1.000   0.5803   0.00629   0.00188  -0.1028   0.7607   0.8451
   1.250   0.6058   0.00624   0.00186  -0.1022   0.7507   0.8660
   1.500   0.6299   0.00612   0.00185  -0.1012   0.7392   0.9054
   1.750   0.6650   0.00607   0.00182  -0.1027   0.7271   1.0000
   2.000   0.6927   0.00616   0.00184  -0.1027   0.7143   1.0000
   2.250   0.7200   0.00626   0.00190  -0.1026   0.6999   1.0000
   2.500   0.7470   0.00637   0.00195  -0.1025   0.6846   1.0000
   2.750   0.7736   0.00650   0.00201  -0.1022   0.6674   1.0000
   3.000   0.7999   0.00664   0.00209  -0.1019   0.6472   1.0000
   3.250   0.8256   0.00682   0.00218  -0.1015   0.6240   1.0000
   3.500   0.8508   0.00704   0.00232  -0.1010   0.5952   1.0000
   3.750   0.8749   0.00732   0.00246  -0.1003   0.5594   1.0000
   4.000   0.8981   0.00769   0.00265  -0.0995   0.5163   1.0000
   4.250   0.9206   0.00813   0.00288  -0.0986   0.4684   1.0000
   4.500   0.9425   0.00865   0.00319  -0.0976   0.4201   1.0000
   4.750   0.9646   0.00917   0.00351  -0.0968   0.3733   1.0000
   5.000   0.9867   0.00970   0.00384  -0.0959   0.3299   1.0000
   5.250   1.0096   0.01016   0.00417  -0.0952   0.3007   1.0000
   5.500   1.0326   0.01062   0.00451  -0.0946   0.2756   1.0000
   5.750   1.0557   0.01105   0.00487  -0.0939   0.2546   1.0000
   6.000   1.0797   0.01140   0.00519  -0.0934   0.2372   1.0000
   6.250   1.1027   0.01183   0.00552  -0.0927   0.2119   1.0000
   6.500   1.1249   0.01234   0.00586  -0.0920   0.1766   1.0000
   6.750   1.1453   0.01302   0.00630  -0.0910   0.1352   1.0000
   7.000   1.1622   0.01403   0.00700  -0.0895   0.0831   1.0000
   7.250   1.1732   0.01568   0.00817  -0.0871   0.0178   1.0000
   7.500   1.1920   0.01656   0.00910  -0.0856   0.0091   1.0000
   7.750   1.2116   0.01732   0.00994  -0.0842   0.0076   1.0000
   8.000   1.2296   0.01822   0.01097  -0.0826   0.0069   1.0000
   8.250   1.2447   0.01934   0.01225  -0.0806   0.0066   1.0000
   8.500   1.2564   0.02067   0.01374  -0.0781   0.0064   1.0000
   8.750   1.2651   0.02211   0.01533  -0.0751   0.0064   1.0000
   9.000   1.2714   0.02353   0.01688  -0.0718   0.0064   1.0000
   9.250   1.2775   0.02505   0.01852  -0.0686   0.0064   1.0000
   9.500   1.2843   0.02667   0.02027  -0.0657   0.0064   1.0000
   9.750   1.2945   0.02798   0.02170  -0.0634   0.0063   1.0000
  10.000   1.3049   0.02926   0.02313  -0.0613   0.0061   1.0000
  10.250   1.3149   0.03054   0.02454  -0.0592   0.0059   1.0000
  10.500   1.3232   0.03211   0.02626  -0.0571   0.0057   1.0000
  10.750   1.3289   0.03432   0.02864  -0.0548   0.0057   1.0000
  11.000   1.3340   0.03658   0.03108  -0.0526   0.0056   1.0000
  11.250   1.3367   0.03925   0.03396  -0.0504   0.0057   1.0000
  11.500   1.3375   0.04195   0.03688  -0.0483   0.0056   1.0000
  11.750   1.3351   0.04501   0.04016  -0.0462   0.0055   1.0000
  12.000   1.3285   0.04864   0.04404  -0.0444   0.0056   1.0000
  12.250   1.3196   0.05246   0.04811  -0.0429   0.0056   1.0000
  12.500   1.3060   0.05705   0.05295  -0.0418   0.0057   1.0000
  12.750   1.2905   0.06199   0.05813  -0.0415   0.0058   1.0000
  13.000   1.2737   0.06737   0.06373  -0.0420   0.0059   1.0000
  13.250   1.2550   0.07336   0.06993  -0.0434   0.0060   1.0000
  13.500   1.2338   0.08026   0.07704  -0.0457   0.0061   1.0000
  13.750   1.1030   0.09057   0.08774  -0.0483   0.0059   1.0000
  14.000   1.0818   0.09795   0.09530  -0.0521   0.0059   1.0000
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