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HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/8 AIRFOIL (hq158-il)
Reynolds number: 200,000
Max Cl/Cd: 60.74 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq158-il-200000-n5.txt
Download as CSV file: xf-hq158-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4194   0.09821   0.09486  -0.0136   1.0000   0.0101
  -9.750  -0.5087   0.10323   0.09962  -0.0109   1.0000   0.0104
  -9.500  -0.5086   0.09881   0.09524  -0.0126   1.0000   0.0100
  -9.250  -0.5078   0.09470   0.09117  -0.0144   1.0000   0.0098
  -9.000  -0.5075   0.09050   0.08700  -0.0164   1.0000   0.0096
  -8.750  -0.5084   0.08604   0.08258  -0.0186   1.0000   0.0094
  -8.500  -0.5089   0.08189   0.07848  -0.0209   1.0000   0.0092
  -8.250  -0.5120   0.07731   0.07395  -0.0237   1.0000   0.0090
  -8.000  -0.5180   0.07241   0.06912  -0.0273   1.0000   0.0089
  -7.750  -0.5226   0.06656   0.06328  -0.0333   1.0000   0.0087
  -7.500  -0.5234   0.06104   0.05769  -0.0372   1.0000   0.0085
  -7.250  -0.5225   0.05555   0.05208  -0.0398   1.0000   0.0083
  -7.000  -0.5190   0.05026   0.04661  -0.0413   1.0000   0.0081
  -6.750  -0.5137   0.04495   0.04106  -0.0418   1.0000   0.0080
  -6.500  -0.5060   0.04000   0.03581  -0.0414   1.0000   0.0078
  -6.250  -0.4965   0.03517   0.03060  -0.0403   1.0000   0.0077
  -6.000  -0.4850   0.03079   0.02577  -0.0388   1.0000   0.0077
  -5.750  -0.4713   0.02717   0.02169  -0.0371   1.0000   0.0080
  -5.500  -0.4486   0.02401   0.01802  -0.0367   0.9978   0.0086
  -5.250  -0.4156   0.02216   0.01575  -0.0381   0.9928   0.0103
  -5.000  -0.3838   0.01969   0.01276  -0.0391   0.9878   0.0114
  -4.750  -0.3524   0.01729   0.01003  -0.0400   0.9834   0.0122
  -4.500  -0.3213   0.01585   0.00844  -0.0408   0.9779   0.0134
  -4.250  -0.2880   0.01475   0.00721  -0.0420   0.9736   0.0154
  -4.000  -0.2566   0.01413   0.00648  -0.0429   0.9670   0.0192
  -3.750  -0.2246   0.01305   0.00530  -0.0439   0.9611   0.0242
  -3.500  -0.1934   0.01238   0.00455  -0.0446   0.9540   0.0354
  -3.250  -0.1613   0.01184   0.00404  -0.0457   0.9475   0.0638
  -3.000  -0.1317   0.01122   0.00365  -0.0465   0.9395   0.1209
  -2.750  -0.1017   0.01039   0.00327  -0.0475   0.9326   0.2449
  -2.500  -0.0757   0.00956   0.00303  -0.0476   0.9236   0.4119
  -2.250  -0.0488   0.00905   0.00296  -0.0474   0.9160   0.5507
  -2.000  -0.0217   0.00884   0.00290  -0.0470   0.9077   0.6297
  -1.750   0.0052   0.00871   0.00286  -0.0465   0.8992   0.6789
  -1.500   0.0322   0.00861   0.00282  -0.0459   0.8914   0.7251
  -1.250   0.0574   0.00854   0.00280  -0.0449   0.8814   0.7599
  -1.000   0.0833   0.00847   0.00273  -0.0441   0.8706   0.7855
  -0.750   0.1091   0.00841   0.00263  -0.0433   0.8593   0.8081
  -0.500   0.1354   0.00835   0.00254  -0.0426   0.8480   0.8246
  -0.250   0.1619   0.00830   0.00245  -0.0421   0.8364   0.8392
   0.000   0.1884   0.00824   0.00238  -0.0415   0.8238   0.8550
   0.250   0.2158   0.00819   0.00232  -0.0411   0.8116   0.8727
   0.500   0.2450   0.00814   0.00228  -0.0412   0.7996   0.8933
   1.000   0.3166   0.00808   0.00222  -0.0442   0.7739   0.9508
   1.250   0.3549   0.00808   0.00221  -0.0465   0.7599   0.9992
   1.500   0.3808   0.00816   0.00222  -0.0461   0.7446   1.0000
   1.750   0.4066   0.00824   0.00224  -0.0456   0.7276   1.0000
   2.000   0.4325   0.00834   0.00230  -0.0452   0.7097   1.0000
   2.250   0.4584   0.00844   0.00240  -0.0447   0.6899   1.0000
   2.500   0.4842   0.00857   0.00248  -0.0442   0.6675   1.0000
   2.750   0.5098   0.00872   0.00257  -0.0436   0.6407   1.0000
   3.000   0.5348   0.00892   0.00267  -0.0429   0.6045   1.0000
   3.250   0.5588   0.00920   0.00278  -0.0421   0.5529   1.0000
   3.500   0.5812   0.00965   0.00297  -0.0410   0.4829   1.0000
   3.750   0.6031   0.01023   0.00323  -0.0400   0.4104   1.0000
   4.000   0.6257   0.01081   0.00354  -0.0393   0.3403   1.0000
   4.250   0.6479   0.01147   0.00392  -0.0385   0.3011   1.0000
   4.750   0.6966   0.01238   0.00466  -0.0376   0.2180   1.0000
   5.000   0.7201   0.01296   0.00514  -0.0371   0.1715   1.0000
   5.250   0.7425   0.01371   0.00564  -0.0365   0.1170   1.0000
   5.500   0.7654   0.01444   0.00624  -0.0359   0.0833   1.0000
   5.750   0.7881   0.01519   0.00688  -0.0353   0.0587   1.0000
   6.000   0.8113   0.01586   0.00750  -0.0347   0.0406   1.0000
   6.250   0.8343   0.01655   0.00818  -0.0342   0.0268   1.0000
   6.500   0.8564   0.01747   0.00911  -0.0333   0.0157   1.0000
   6.750   0.8778   0.01853   0.01033  -0.0322   0.0117   1.0000
   7.000   0.8988   0.01961   0.01165  -0.0311   0.0098   1.0000
   7.250   0.9183   0.02092   0.01308  -0.0300   0.0083   1.0000
   7.500   0.9382   0.02214   0.01445  -0.0290   0.0068   1.0000
   7.750   0.9579   0.02346   0.01595  -0.0278   0.0060   1.0000
   8.000   0.9764   0.02506   0.01776  -0.0266   0.0056   1.0000
   8.250   0.9941   0.02685   0.01978  -0.0253   0.0053   1.0000
   8.500   1.0108   0.02884   0.02203  -0.0239   0.0050   1.0000
   8.750   1.0257   0.03108   0.02458  -0.0224   0.0049   1.0000
   9.000   1.0381   0.03363   0.02747  -0.0208   0.0048   1.0000
   9.250   1.0471   0.03649   0.03071  -0.0189   0.0047   1.0000
   9.500   1.0513   0.03968   0.03429  -0.0168   0.0046   1.0000
   9.750   1.0500   0.04314   0.03814  -0.0144   0.0046   1.0000
  10.000   1.0419   0.04658   0.04192  -0.0116   0.0046   1.0000
  10.250   1.0270   0.05023   0.04589  -0.0088   0.0047   1.0000
  10.500   1.0103   0.05407   0.04997  -0.0074   0.0047   1.0000
  10.750   0.9912   0.05883   0.05498  -0.0077   0.0048   1.0000
  11.000   0.9702   0.06470   0.06106  -0.0100   0.0048   1.0000
  11.250   0.9492   0.07183   0.06838  -0.0145   0.0049   1.0000
  11.500   0.9273   0.08128   0.07799  -0.0218   0.0049   1.0000
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