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HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/8 AIRFOIL (hq158-il)
Reynolds number: 500,000
Max Cl/Cd: 86.77 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq158-il-500000.txt
Download as CSV file: xf-hq158-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5024   0.08240   0.08021  -0.0209   1.0000   0.0146
  -8.250  -0.5047   0.07803   0.07588  -0.0236   1.0000   0.0149
  -8.000  -0.5098   0.07358   0.07148  -0.0265   1.0000   0.0151
  -7.750  -0.5168   0.06817   0.06609  -0.0324   1.0000   0.0148
  -7.500  -0.5180   0.06253   0.06039  -0.0370   1.0000   0.0150
  -7.250  -0.5164   0.05739   0.05515  -0.0398   1.0000   0.0154
  -7.000  -0.5118   0.05260   0.05024  -0.0413   1.0000   0.0160
  -6.750  -0.5038   0.04819   0.04566  -0.0417   1.0000   0.0168
  -6.500  -0.4846   0.04624   0.04350  -0.0408   1.0000   0.0181
  -6.250  -0.4768   0.04308   0.04013  -0.0396   1.0000   0.0182
  -6.000  -0.4709   0.04011   0.03695  -0.0376   1.0000   0.0183
  -5.750  -0.4598   0.03686   0.03345  -0.0365   0.9992   0.0183
  -5.250  -0.4058   0.01982   0.01492  -0.0404   0.9906   0.0112
  -5.000  -0.3720   0.01788   0.01270  -0.0416   0.9871   0.0109
  -4.750  -0.3403   0.01413   0.00849  -0.0425   0.9842   0.0117
  -4.500  -0.3052   0.01267   0.00687  -0.0442   0.9819   0.0129
  -4.250  -0.2726   0.01214   0.00630  -0.0454   0.9770   0.0152
  -4.000  -0.2388   0.01101   0.00505  -0.0466   0.9730   0.0158
  -3.750  -0.2038   0.01021   0.00414  -0.0481   0.9695   0.0178
  -3.500  -0.1733   0.00935   0.00319  -0.0485   0.9626   0.0255
  -3.250  -0.1415   0.00875   0.00270  -0.0494   0.9567   0.0621
  -3.000  -0.1125   0.00832   0.00240  -0.0498   0.9485   0.1063
  -2.750  -0.0860   0.00736   0.00209  -0.0501   0.9406   0.2805
  -2.500  -0.0640   0.00637   0.00192  -0.0494   0.9298   0.5164
  -2.250  -0.0388   0.00612   0.00185  -0.0486   0.9190   0.5939
  -2.000  -0.0130   0.00600   0.00177  -0.0479   0.9076   0.6377
  -1.750   0.0128   0.00593   0.00168  -0.0472   0.8960   0.6689
  -1.500   0.0387   0.00587   0.00164  -0.0465   0.8856   0.7000
  -1.250   0.0646   0.00582   0.00162  -0.0459   0.8751   0.7273
  -1.000   0.0906   0.00579   0.00160  -0.0453   0.8650   0.7518
  -0.750   0.1161   0.00576   0.00158  -0.0445   0.8543   0.7787
  -0.500   0.1418   0.00574   0.00155  -0.0438   0.8427   0.7985
  -0.250   0.1678   0.00572   0.00153  -0.0431   0.8322   0.8173
   0.000   0.1937   0.00567   0.00151  -0.0425   0.8216   0.8358
   0.250   0.2196   0.00562   0.00148  -0.0419   0.8103   0.8531
   0.500   0.2457   0.00558   0.00145  -0.0414   0.7991   0.8699
   0.750   0.2717   0.00551   0.00142  -0.0407   0.7880   0.8900
   1.000   0.2995   0.00545   0.00141  -0.0405   0.7770   0.9182
   1.250   0.3384   0.00542   0.00141  -0.0428   0.7646   0.9560
   1.500   0.3817   0.00544   0.00141  -0.0462   0.7509   0.9970
   1.750   0.4092   0.00551   0.00142  -0.0462   0.7357   1.0000
   2.000   0.4352   0.00559   0.00146  -0.0458   0.7187   1.0000
   2.250   0.4611   0.00569   0.00149  -0.0453   0.6981   1.0000
   2.500   0.4869   0.00581   0.00156  -0.0449   0.6726   1.0000
   2.750   0.5122   0.00597   0.00162  -0.0443   0.6406   1.0000
   3.000   0.5371   0.00619   0.00169  -0.0437   0.5955   1.0000
   3.250   0.5607   0.00655   0.00180  -0.0429   0.5313   1.0000
   3.500   0.5835   0.00707   0.00198  -0.0420   0.4519   1.0000
   3.750   0.6073   0.00754   0.00224  -0.0414   0.3893   1.0000
   4.000   0.6310   0.00805   0.00248  -0.0409   0.3246   1.0000
   4.250   0.6551   0.00854   0.00280  -0.0403   0.2921   1.0000
   4.500   0.6804   0.00888   0.00302  -0.0400   0.2456   1.0000
   4.750   0.7049   0.00933   0.00331  -0.0396   0.2063   1.0000
   5.500   0.7741   0.01132   0.00458  -0.0379   0.0557   1.0000
   5.750   0.7984   0.01184   0.00505  -0.0374   0.0408   1.0000
   6.000   0.8226   0.01235   0.00554  -0.0368   0.0288   1.0000
   6.250   0.8451   0.01323   0.00637  -0.0359   0.0130   1.0000
   6.500   0.8659   0.01441   0.00773  -0.0345   0.0105   1.0000
   6.750   0.8877   0.01537   0.00885  -0.0335   0.0098   1.0000
   7.000   0.9093   0.01633   0.00993  -0.0324   0.0090   1.0000
   7.250   0.9328   0.01689   0.01054  -0.0319   0.0079   1.0000
   7.500   0.9538   0.01791   0.01165  -0.0308   0.0073   1.0000
   7.750   0.9730   0.01932   0.01320  -0.0296   0.0068   1.0000
   8.000   0.9879   0.02196   0.01611  -0.0277   0.0064   1.0000
   8.250   1.0010   0.02555   0.02010  -0.0256   0.0061   1.0000
   8.500   1.0167   0.02797   0.02283  -0.0240   0.0060   1.0000
   8.750   1.0274   0.03118   0.02642  -0.0219   0.0060   1.0000
   9.000   1.0273   0.03634   0.03204  -0.0190   0.0062   1.0000
   9.250   1.0400   0.03798   0.03386  -0.0175   0.0063   1.0000
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