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HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il)
Reynolds number: 500,000
Max Cl/Cd: 67.33 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1585-il-500000-n5.txt
Download as CSV file: xf-hq1585-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/8.5 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5896   0.08653   0.08431  -0.0165   1.0000   0.0059
 -10.000  -0.6098   0.07773   0.07557  -0.0218   1.0000   0.0057
  -9.750  -0.6290   0.06889   0.06679  -0.0281   1.0000   0.0056
  -9.250  -0.7651   0.02976   0.02631  -0.0463   1.0000   0.0051
  -9.000  -0.7557   0.02598   0.02206  -0.0457   1.0000   0.0054
  -8.750  -0.7401   0.02344   0.01914  -0.0449   1.0000   0.0058
  -8.500  -0.7210   0.02180   0.01723  -0.0443   1.0000   0.0060
  -8.250  -0.7046   0.01938   0.01446  -0.0433   1.0000   0.0064
  -8.000  -0.6835   0.01838   0.01329  -0.0426   1.0000   0.0068
  -7.750  -0.6616   0.01770   0.01253  -0.0419   1.0000   0.0073
  -7.500  -0.6345   0.01693   0.01164  -0.0422   0.9965   0.0078
  -7.250  -0.6027   0.01599   0.01055  -0.0435   0.9896   0.0086
  -7.000  -0.5707   0.01507   0.00946  -0.0448   0.9817   0.0094
  -6.750  -0.5377   0.01449   0.00875  -0.0462   0.9734   0.0101
  -6.500  -0.5054   0.01375   0.00794  -0.0476   0.9643   0.0117
  -6.250  -0.4735   0.01334   0.00748  -0.0487   0.9541   0.0130
  -6.000  -0.4429   0.01282   0.00686  -0.0494   0.9435   0.0143
  -5.750  -0.4139   0.01239   0.00632  -0.0498   0.9322   0.0153
  -5.500  -0.3865   0.01197   0.00581  -0.0498   0.9211   0.0163
  -5.250  -0.3609   0.01133   0.00508  -0.0495   0.9100   0.0182
  -5.000  -0.3346   0.01096   0.00465  -0.0492   0.8995   0.0195
  -4.750  -0.3081   0.01067   0.00427  -0.0490   0.8900   0.0212
  -4.250  -0.2548   0.01010   0.00351  -0.0485   0.8720   0.0236
  -4.000  -0.2281   0.00977   0.00310  -0.0482   0.8640   0.0252
  -3.750  -0.2012   0.00948   0.00276  -0.0480   0.8562   0.0288
  -3.500  -0.1740   0.00927   0.00250  -0.0478   0.8492   0.0334
  -3.250  -0.1469   0.00905   0.00228  -0.0477   0.8423   0.0445
  -3.000  -0.1196   0.00884   0.00208  -0.0476   0.8362   0.0603
  -2.750  -0.0926   0.00854   0.00188  -0.0475   0.8300   0.0941
  -2.500  -0.0660   0.00815   0.00169  -0.0475   0.8244   0.1634
  -2.250  -0.0389   0.00785   0.00156  -0.0475   0.8184   0.2200
  -2.000  -0.0124   0.00746   0.00143  -0.0475   0.8120   0.3047
  -1.750   0.0130   0.00686   0.00132  -0.0474   0.8038   0.4494
  -1.500   0.0389   0.00655   0.00128  -0.0470   0.7947   0.5462
  -1.250   0.0659   0.00643   0.00125  -0.0468   0.7855   0.5886
  -1.000   0.0931   0.00634   0.00124  -0.0465   0.7766   0.6252
  -0.750   0.1200   0.00628   0.00123  -0.0462   0.7661   0.6597
  -0.500   0.1472   0.00626   0.00122  -0.0459   0.7543   0.6805
  -0.250   0.1747   0.00626   0.00120  -0.0457   0.7420   0.6971
   0.000   0.2023   0.00625   0.00120  -0.0455   0.7301   0.7123
   0.250   0.2298   0.00625   0.00122  -0.0453   0.7186   0.7291
   0.500   0.2572   0.00626   0.00123  -0.0451   0.7073   0.7453
   0.750   0.2847   0.00628   0.00125  -0.0449   0.6946   0.7582
   1.000   0.3119   0.00631   0.00127  -0.0447   0.6786   0.7705
   1.250   0.3390   0.00635   0.00129  -0.0444   0.6608   0.7827
   1.500   0.3656   0.00643   0.00131  -0.0440   0.6356   0.7936
   1.750   0.3910   0.00662   0.00134  -0.0434   0.5892   0.8027
   2.000   0.4152   0.00698   0.00142  -0.0428   0.5112   0.8113
   2.250   0.4392   0.00741   0.00155  -0.0421   0.4336   0.8207
   2.500   0.4640   0.00775   0.00171  -0.0416   0.3768   0.8311
   2.750   0.4889   0.00804   0.00188  -0.0412   0.3297   0.8437
   3.000   0.5140   0.00826   0.00204  -0.0407   0.2968   0.8604
   3.250   0.5378   0.00852   0.00221  -0.0399   0.2551   0.8864
   3.500   0.5643   0.00874   0.00239  -0.0396   0.2204   0.9324
   3.750   0.5999   0.00904   0.00260  -0.0416   0.1888   1.0000
   4.000   0.6253   0.00946   0.00284  -0.0413   0.1456   1.0000
   4.250   0.6498   0.01003   0.00315  -0.0410   0.0964   1.0000
   4.500   0.6744   0.01058   0.00350  -0.0407   0.0560   1.0000
   4.750   0.7001   0.01096   0.00381  -0.0404   0.0435   1.0000
   5.000   0.7261   0.01129   0.00415  -0.0401   0.0384   1.0000
   5.250   0.7523   0.01157   0.00447  -0.0399   0.0356   1.0000
   5.500   0.7785   0.01185   0.00479  -0.0397   0.0336   1.0000
   5.750   0.8045   0.01216   0.00513  -0.0395   0.0321   1.0000
   6.000   0.8300   0.01252   0.00549  -0.0392   0.0290   1.0000
   6.250   0.8550   0.01296   0.00596  -0.0388   0.0253   1.0000
   6.500   0.8811   0.01320   0.00627  -0.0386   0.0236   1.0000
   6.750   0.9069   0.01347   0.00658  -0.0384   0.0203   1.0000
   7.000   0.9319   0.01387   0.00695  -0.0381   0.0139   1.0000
   7.250   0.9556   0.01445   0.00746  -0.0376   0.0094   1.0000
   7.500   0.9790   0.01510   0.00815  -0.0370   0.0073   1.0000
   7.750   1.0025   0.01570   0.00883  -0.0364   0.0066   1.0000
   8.000   1.0258   0.01631   0.00954  -0.0358   0.0060   1.0000
   8.250   1.0484   0.01699   0.01035  -0.0351   0.0057   1.0000
   8.500   1.0704   0.01774   0.01121  -0.0344   0.0053   1.0000
   8.750   1.0917   0.01857   0.01214  -0.0335   0.0050   1.0000
   9.000   1.1121   0.01948   0.01317  -0.0326   0.0047   1.0000
   9.250   1.1311   0.02055   0.01437  -0.0316   0.0045   1.0000
   9.500   1.1473   0.02196   0.01594  -0.0302   0.0042   1.0000
   9.750   1.1587   0.02399   0.01821  -0.0282   0.0039   1.0000
  10.000   1.1743   0.02533   0.01971  -0.0268   0.0039   1.0000
  10.250   1.1895   0.02662   0.02116  -0.0255   0.0038   1.0000
  10.500   1.2033   0.02796   0.02271  -0.0240   0.0037   1.0000
  10.750   1.2158   0.02932   0.02425  -0.0224   0.0036   1.0000
  11.000   1.2250   0.03084   0.02594  -0.0205   0.0035   1.0000
  11.250   1.2286   0.03246   0.02775  -0.0179   0.0034   1.0000
  11.500   1.2316   0.03400   0.02946  -0.0154   0.0032   1.0000
  11.750   1.2298   0.03605   0.03169  -0.0130   0.0032   1.0000
  12.000   1.2281   0.03818   0.03400  -0.0112   0.0031   1.0000
  12.250   1.2222   0.04092   0.03694  -0.0098   0.0030   1.0000
  12.500   1.2139   0.04415   0.04038  -0.0090   0.0030   1.0000
  12.750   1.2046   0.04777   0.04418  -0.0090   0.0030   1.0000
  13.000   1.1902   0.05245   0.04908  -0.0099   0.0030   1.0000
  13.250   1.1759   0.05770   0.05452  -0.0120   0.0030   1.0000
  13.500   1.1597   0.06395   0.06095  -0.0153   0.0030   1.0000
  13.750   1.1399   0.07181   0.06901  -0.0203   0.0030   1.0000
  14.000   1.1201   0.08078   0.07816  -0.0263   0.0030   1.0000
  14.250   1.0900   0.09309   0.09066  -0.0343   0.0031   1.0000
  14.500   1.0529   0.10760   0.10532  -0.0429   0.0032   1.0000
  14.750   1.0250   0.12013   0.11795  -0.0498   0.0032   1.0000
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