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HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/8 AIRFOIL (hq158-il)
Reynolds number: 500,000
Max Cl/Cd: 69.99 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq158-il-500000-n5.txt
Download as CSV file: xf-hq158-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/8 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5156   0.08247   0.08028  -0.0195   1.0000   0.0044
  -8.500  -0.5175   0.07810   0.07594  -0.0220   1.0000   0.0043
  -8.250  -0.5233   0.07317   0.07106  -0.0252   1.0000   0.0042
  -8.000  -0.5330   0.06747   0.06541  -0.0308   1.0000   0.0042
  -7.750  -0.5366   0.06087   0.05874  -0.0369   1.0000   0.0040
  -7.500  -0.5374   0.05489   0.05265  -0.0402   1.0000   0.0039
  -7.250  -0.5369   0.04865   0.04623  -0.0420   1.0000   0.0038
  -7.000  -0.5351   0.04214   0.03947  -0.0424   1.0000   0.0036
  -6.750  -0.5287   0.02802   0.02448  -0.0442   0.9909   0.0033
  -6.500  -0.5054   0.02070   0.01623  -0.0453   0.9832   0.0032
  -6.250  -0.4771   0.01829   0.01342  -0.0461   0.9766   0.0033
  -6.000  -0.4473   0.01645   0.01127  -0.0470   0.9706   0.0035
  -5.750  -0.4178   0.01509   0.00967  -0.0476   0.9631   0.0038
  -5.500  -0.3881   0.01390   0.00828  -0.0481   0.9554   0.0044
  -5.250  -0.3588   0.01291   0.00707  -0.0485   0.9466   0.0049
  -5.000  -0.3307   0.01220   0.00623  -0.0486   0.9362   0.0054
  -4.750  -0.3040   0.01130   0.00520  -0.0485   0.9256   0.0066
  -4.500  -0.2769   0.01084   0.00467  -0.0485   0.9154   0.0080
  -4.000  -0.2240   0.00992   0.00351  -0.0478   0.8950   0.0105
  -3.750  -0.1977   0.00950   0.00298  -0.0474   0.8852   0.0135
  -3.500  -0.1711   0.00920   0.00262  -0.0471   0.8758   0.0186
  -3.250  -0.1445   0.00892   0.00231  -0.0468   0.8662   0.0334
  -3.000  -0.1178   0.00871   0.00210  -0.0466   0.8568   0.0477
  -2.750  -0.0911   0.00850   0.00190  -0.0463   0.8475   0.0686
  -2.500  -0.0652   0.00810   0.00170  -0.0461   0.8376   0.1305
  -2.250  -0.0397   0.00760   0.00151  -0.0459   0.8264   0.2307
  -2.000  -0.0141   0.00720   0.00132  -0.0457   0.8129   0.3206
  -1.750   0.0111   0.00679   0.00119  -0.0453   0.7977   0.4301
  -1.500   0.0367   0.00654   0.00111  -0.0449   0.7830   0.5102
  -1.250   0.0624   0.00632   0.00109  -0.0445   0.7704   0.5884
  -1.000   0.0888   0.00621   0.00108  -0.0441   0.7599   0.6381
  -0.750   0.1150   0.00613   0.00107  -0.0436   0.7488   0.6811
  -0.500   0.1416   0.00611   0.00106  -0.0432   0.7348   0.7077
  -0.250   0.1683   0.00610   0.00105  -0.0429   0.7206   0.7284
   0.000   0.1950   0.00610   0.00105  -0.0426   0.7081   0.7485
   0.250   0.2219   0.00611   0.00105  -0.0423   0.6949   0.7637
   0.500   0.2489   0.00614   0.00105  -0.0420   0.6805   0.7753
   0.750   0.2758   0.00617   0.00107  -0.0418   0.6644   0.7869
   1.000   0.3026   0.00622   0.00109  -0.0415   0.6471   0.7992
   1.250   0.3292   0.00627   0.00113  -0.0411   0.6281   0.8122
   1.500   0.3553   0.00635   0.00116  -0.0407   0.6026   0.8262
   1.750   0.3810   0.00645   0.00121  -0.0402   0.5707   0.8414
   2.000   0.4062   0.00658   0.00127  -0.0397   0.5345   0.8592
   2.250   0.4308   0.00675   0.00137  -0.0390   0.4896   0.8825
   2.500   0.4587   0.00698   0.00150  -0.0390   0.4359   0.9227
   2.750   0.4995   0.00739   0.00168  -0.0422   0.3699   1.0000
   3.000   0.5239   0.00784   0.00186  -0.0418   0.3138   1.0000
   3.250   0.5492   0.00817   0.00209  -0.0415   0.2977   1.0000
   3.500   0.5765   0.00826   0.00226  -0.0414   0.2766   1.0000
   3.750   0.6019   0.00860   0.00243  -0.0411   0.2392   1.0000
   4.000   0.6268   0.00902   0.00266  -0.0407   0.1964   1.0000
   4.250   0.6519   0.00940   0.00291  -0.0404   0.1609   1.0000
   4.500   0.6766   0.00985   0.00319  -0.0400   0.1220   1.0000
   4.750   0.6997   0.01053   0.00359  -0.0395   0.0690   1.0000
   5.000   0.7243   0.01099   0.00398  -0.0391   0.0467   1.0000
   5.250   0.7496   0.01136   0.00432  -0.0388   0.0359   1.0000
   5.500   0.7745   0.01178   0.00469  -0.0384   0.0240   1.0000
   5.750   0.7994   0.01219   0.00510  -0.0380   0.0162   1.0000
   6.000   0.8234   0.01277   0.00564  -0.0374   0.0065   1.0000
   6.250   0.8474   0.01335   0.00625  -0.0368   0.0042   1.0000
   6.500   0.8717   0.01388   0.00688  -0.0363   0.0037   1.0000
   6.750   0.8956   0.01446   0.00760  -0.0357   0.0033   1.0000
   7.000   0.9189   0.01514   0.00840  -0.0350   0.0030   1.0000
   7.250   0.9415   0.01590   0.00927  -0.0342   0.0028   1.0000
   7.500   0.9633   0.01678   0.01029  -0.0333   0.0026   1.0000
   7.750   0.9843   0.01778   0.01142  -0.0323   0.0024   1.0000
   8.000   1.0046   0.01887   0.01266  -0.0313   0.0023   1.0000
   8.250   1.0237   0.02014   0.01410  -0.0301   0.0022   1.0000
   8.500   1.0421   0.02153   0.01566  -0.0288   0.0022   1.0000
   8.750   1.0593   0.02312   0.01746  -0.0274   0.0021   1.0000
   9.000   1.0754   0.02483   0.01941  -0.0260   0.0021   1.0000
   9.250   1.0899   0.02674   0.02157  -0.0244   0.0021   1.0000
   9.500   1.1015   0.02899   0.02415  -0.0226   0.0021   1.0000
   9.750   1.1102   0.03144   0.02692  -0.0205   0.0021   1.0000
  10.000   1.1149   0.03411   0.02991  -0.0182   0.0021   1.0000
  10.250   1.1157   0.03689   0.03301  -0.0157   0.0021   1.0000
  10.500   1.1059   0.03988   0.03628  -0.0120   0.0021   1.0000
  10.750   1.0932   0.04288   0.03953  -0.0089   0.0021   1.0000
  11.000   1.0776   0.04646   0.04336  -0.0070   0.0022   1.0000
  11.250   1.0600   0.05071   0.04784  -0.0066   0.0022   1.0000
  11.500   1.0411   0.05584   0.05316  -0.0079   0.0022   1.0000
  11.750   1.0198   0.06243   0.05995  -0.0113   0.0022   1.0000
  12.000   0.9975   0.07099   0.06869  -0.0174   0.0022   1.0000
  12.250   0.9772   0.08170   0.07957  -0.0255   0.0022   1.0000
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