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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 500,000
Max Cl/Cd: 118.97 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3510-il-500000.txt
Download as CSV file: xf-hq3510-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3365   0.09783   0.09565  -0.0384   1.0000   0.0142
  -9.000  -0.3417   0.09572   0.09359  -0.0370   1.0000   0.0145
  -8.750  -0.3534   0.09426   0.09219  -0.0342   1.0000   0.0146
  -8.500  -0.3397   0.08999   0.08792  -0.0388   0.9980   0.0152
  -8.250  -0.3246   0.08532   0.08326  -0.0443   0.9949   0.0159
  -8.000  -0.3104   0.08053   0.07847  -0.0501   0.9907   0.0166
  -7.750  -0.2941   0.07500   0.07295  -0.0580   0.9858   0.0175
  -7.500  -0.2695   0.06816   0.06611  -0.0708   0.9789   0.0185
  -7.250  -0.2402   0.05948   0.05734  -0.0871   0.9731   0.0187
  -7.000  -0.2117   0.05246   0.05011  -0.0976   0.9700   0.0188
  -6.750  -0.2060   0.04261   0.03999  -0.1057   0.9600   0.0196
  -6.500  -0.1824   0.03940   0.03668  -0.1091   0.9560   0.0203
  -6.250  -0.1647   0.03701   0.03417  -0.1100   0.9476   0.0212
  -6.000  -0.1415   0.03398   0.03091  -0.1117   0.9422   0.0225
  -5.750  -0.1217   0.03103   0.02770  -0.1118   0.9337   0.0247
  -5.500  -0.0942   0.01583   0.01236  -0.1037   0.9109   0.0272
  -5.250  -0.0767   0.02207   0.01767  -0.1108   0.9197   0.0186
  -5.000  -0.0549   0.01749   0.01256  -0.1107   0.9143   0.0171
  -4.750  -0.0311   0.01461   0.00925  -0.1097   0.9075   0.0156
  -4.500  -0.0052   0.01289   0.00726  -0.1091   0.9023   0.0151
  -4.250   0.0206   0.01187   0.00610  -0.1086   0.8965   0.0154
  -4.000   0.0468   0.01112   0.00524  -0.1081   0.8905   0.0162
  -3.750   0.0739   0.01055   0.00455  -0.1079   0.8855   0.0176
  -3.500   0.1002   0.01001   0.00393  -0.1075   0.8790   0.0195
  -3.250   0.1277   0.00959   0.00347  -0.1073   0.8737   0.0249
  -3.000   0.1548   0.00920   0.00312  -0.1072   0.8675   0.0463
  -2.750   0.1823   0.00901   0.00289  -0.1071   0.8615   0.0582
  -2.500   0.2099   0.00883   0.00268  -0.1070   0.8555   0.0708
  -2.250   0.2370   0.00854   0.00249  -0.1069   0.8483   0.1052
  -2.000   0.2617   0.00733   0.00224  -0.1071   0.8411   0.4066
  -1.750   0.2874   0.00691   0.00220  -0.1067   0.8328   0.5555
  -1.500   0.3141   0.00681   0.00218  -0.1063   0.8243   0.6077
  -1.250   0.3414   0.00677   0.00212  -0.1060   0.8168   0.6392
  -1.000   0.3684   0.00675   0.00210  -0.1057   0.8083   0.6632
  -0.750   0.3954   0.00673   0.00209  -0.1053   0.8009   0.6924
  -0.500   0.4218   0.00672   0.00212  -0.1048   0.7923   0.7213
  -0.250   0.4483   0.00673   0.00214  -0.1043   0.7839   0.7470
   0.000   0.4749   0.00673   0.00212  -0.1038   0.7755   0.7648
   0.250   0.5022   0.00673   0.00210  -0.1036   0.7659   0.7747
   0.500   0.5294   0.00673   0.00208  -0.1034   0.7569   0.7844
   0.750   0.5565   0.00673   0.00206  -0.1031   0.7481   0.7943
   1.000   0.5835   0.00673   0.00207  -0.1029   0.7389   0.8050
   1.250   0.6105   0.00674   0.00207  -0.1026   0.7297   0.8167
   1.500   0.6371   0.00676   0.00208  -0.1023   0.7195   0.8296
   1.750   0.6632   0.00674   0.00209  -0.1019   0.7082   0.8442
   2.000   0.6888   0.00671   0.00213  -0.1013   0.6972   0.8622
   2.250   0.7132   0.00666   0.00214  -0.1004   0.6852   0.8909
   2.500   0.7468   0.00657   0.00213  -0.1015   0.6709   1.0000
   2.750   0.7743   0.00669   0.00218  -0.1015   0.6561   1.0000
   3.000   0.8011   0.00683   0.00227  -0.1014   0.6391   1.0000
   3.250   0.8273   0.00698   0.00235  -0.1011   0.6193   1.0000
   3.500   0.8530   0.00717   0.00245  -0.1007   0.5953   1.0000
   3.750   0.8776   0.00741   0.00257  -0.1001   0.5658   1.0000
   4.000   0.9015   0.00771   0.00274  -0.0994   0.5295   1.0000
   4.250   0.9241   0.00810   0.00295  -0.0986   0.4875   1.0000
   4.500   0.9460   0.00857   0.00320  -0.0976   0.4431   1.0000
   4.750   0.9677   0.00906   0.00350  -0.0966   0.4002   1.0000
   5.000   0.9897   0.00956   0.00383  -0.0957   0.3602   1.0000
   5.250   1.0117   0.01005   0.00415  -0.0949   0.3255   1.0000
   5.750   1.0575   0.01090   0.00480  -0.0934   0.2828   1.0000
   6.000   1.0809   0.01127   0.00514  -0.0928   0.2689   1.0000
   6.250   1.1040   0.01165   0.00548  -0.0921   0.2519   1.0000
   6.500   1.1272   0.01201   0.00580  -0.0915   0.2357   1.0000
   6.750   1.1499   0.01240   0.00613  -0.0908   0.2179   1.0000
   7.000   1.1727   0.01278   0.00646  -0.0901   0.1999   1.0000
   7.250   1.1951   0.01318   0.00680  -0.0894   0.1797   1.0000
   7.500   1.2156   0.01371   0.00723  -0.0883   0.1520   1.0000
   7.750   1.2327   0.01452   0.00780  -0.0869   0.1140   1.0000
   8.000   1.2481   0.01546   0.00851  -0.0851   0.0788   1.0000
   8.250   1.2587   0.01679   0.00951  -0.0827   0.0354   1.0000
   8.500   1.2687   0.01815   0.01071  -0.0800   0.0111   1.0000
   8.750   1.2828   0.01904   0.01166  -0.0778   0.0085   1.0000
   9.000   1.2967   0.01983   0.01257  -0.0755   0.0078   1.0000
   9.250   1.3099   0.02065   0.01349  -0.0733   0.0075   1.0000
   9.500   1.3214   0.02156   0.01454  -0.0709   0.0071   1.0000
   9.750   1.3315   0.02257   0.01566  -0.0684   0.0069   1.0000
  10.000   1.3396   0.02372   0.01693  -0.0657   0.0067   1.0000
  10.250   1.3465   0.02497   0.01829  -0.0630   0.0066   1.0000
  10.500   1.3539   0.02621   0.01963  -0.0607   0.0064   1.0000
  10.750   1.3589   0.02767   0.02120  -0.0582   0.0062   1.0000
  11.000   1.3641   0.02916   0.02279  -0.0559   0.0059   1.0000
  11.250   1.3660   0.03099   0.02473  -0.0536   0.0057   1.0000
  11.500   1.3651   0.03316   0.02702  -0.0512   0.0055   1.0000
  11.750   1.3644   0.03547   0.02945  -0.0491   0.0054   1.0000
  12.000   1.3639   0.03787   0.03199  -0.0473   0.0054   1.0000
  12.250   1.3601   0.04081   0.03507  -0.0455   0.0053   1.0000
  12.500   1.3589   0.04361   0.03803  -0.0441   0.0053   1.0000
  12.750   1.3580   0.04650   0.04106  -0.0429   0.0053   1.0000
  13.000   1.3535   0.05008   0.04484  -0.0418   0.0052   1.0000
  13.250   1.3490   0.05378   0.04873  -0.0410   0.0052   1.0000
  13.500   1.3431   0.05781   0.05295  -0.0405   0.0052   1.0000
  13.750   1.3369   0.06188   0.05720  -0.0405   0.0051   1.0000
  14.000   1.3298   0.06608   0.06158  -0.0409   0.0051   1.0000
  14.250   1.3220   0.07054   0.06623  -0.0418   0.0051   1.0000
  14.500   1.3120   0.07565   0.07153  -0.0431   0.0051   1.0000
  14.750   1.2985   0.08176   0.07784  -0.0446   0.0052   1.0000
  15.000   1.2841   0.08818   0.08445  -0.0472   0.0052   1.0000
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