Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il)
Reynolds number: 200,000
Max Cl/Cd: 75.68 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3015-il-200000.txt
Download as CSV file: xf-hq3015-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/15 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3789   0.11445   0.11084  -0.0564   1.0000   0.0626
 -12.000  -0.5384   0.06810   0.06424  -0.0796   1.0000   0.0354
 -11.750  -0.5611   0.06300   0.05912  -0.0813   1.0000   0.0352
 -11.500  -0.5876   0.05904   0.05513  -0.0814   1.0000   0.0349
 -11.250  -0.6201   0.05685   0.05294  -0.0783   1.0000   0.0348
 -11.000  -0.6536   0.05602   0.05214  -0.0732   1.0000   0.0347
 -10.750  -0.6799   0.05320   0.04921  -0.0727   0.9968   0.0345
 -10.500  -0.6913   0.04716   0.04269  -0.0777   0.9859   0.0345
 -10.250  -0.6916   0.04160   0.03650  -0.0807   0.9765   0.0350
 -10.000  -0.6793   0.03699   0.03137  -0.0830   0.9705   0.0361
  -9.750  -0.6561   0.03536   0.02968  -0.0842   0.9648   0.0375
  -9.500  -0.6296   0.03373   0.02789  -0.0857   0.9594   0.0395
  -9.250  -0.6005   0.03176   0.02534  -0.0879   0.9557   0.0428
  -9.000  -0.5789   0.03009   0.02375  -0.0883   0.9493   0.0457
  -8.750  -0.5487   0.02902   0.02250  -0.0897   0.9448   0.0496
  -8.500  -0.5154   0.02691   0.02008  -0.0919   0.9421   0.0536
  -8.250  -0.4772   0.02615   0.01931  -0.0947   0.9401   0.0583
  -8.000  -0.4577   0.02595   0.01884  -0.0935   0.9316   0.0620
  -7.750  -0.4255   0.02432   0.01726  -0.0953   0.9283   0.0668
  -7.500  -0.3896   0.02354   0.01633  -0.0972   0.9257   0.0715
  -7.250  -0.3670   0.02318   0.01575  -0.0963   0.9183   0.0742
  -7.000  -0.3375   0.02158   0.01421  -0.0971   0.9142   0.0783
  -6.750  -0.3042   0.02082   0.01339  -0.0983   0.9110   0.0826
  -6.500  -0.2796   0.02027   0.01274  -0.0977   0.9048   0.0858
  -6.250  -0.2540   0.01931   0.01177  -0.0974   0.8992   0.0896
  -6.000  -0.2242   0.01860   0.01110  -0.0979   0.8955   0.0952
  -5.750  -0.2016   0.01823   0.01064  -0.0970   0.8890   0.1004
  -5.500  -0.1788   0.01747   0.00996  -0.0963   0.8830   0.1075
  -5.250  -0.1507   0.01687   0.00934  -0.0964   0.8792   0.1175
  -5.000  -0.1313   0.01649   0.00901  -0.0951   0.8720   0.1302
  -4.750  -0.1080   0.01583   0.00850  -0.0945   0.8666   0.1533
  -4.500  -0.0826   0.01500   0.00797  -0.0944   0.8628   0.2117
  -4.250  -0.0672   0.01434   0.00773  -0.0928   0.8550   0.3037
  -4.000  -0.0468   0.01358   0.00765  -0.0918   0.8499   0.4622
  -3.750  -0.0184   0.01350   0.00770  -0.0914   0.8466   0.5324
  -3.500   0.0023   0.01371   0.00795  -0.0899   0.8389   0.5658
  -3.250   0.0303   0.01379   0.00797  -0.0895   0.8342   0.5928
  -3.000   0.0603   0.01385   0.00799  -0.0893   0.8309   0.6129
  -2.750   0.0822   0.01408   0.00821  -0.0881   0.8233   0.6284
  -2.500   0.1102   0.01415   0.00823  -0.0876   0.8185   0.6437
  -2.250   0.1402   0.01419   0.00821  -0.0874   0.8149   0.6588
  -2.000   0.1619   0.01443   0.00845  -0.0861   0.8073   0.6732
  -1.750   0.1893   0.01454   0.00854  -0.0854   0.8024   0.6887
  -1.500   0.2187   0.01458   0.00857  -0.0850   0.7990   0.7001
  -1.250   0.2407   0.01471   0.00871  -0.0839   0.7913   0.7085
  -1.000   0.2693   0.01468   0.00863  -0.0837   0.7866   0.7168
  -0.750   0.2998   0.01460   0.00849  -0.0838   0.7831   0.7249
  -0.500   0.3214   0.01475   0.00867  -0.0826   0.7752   0.7340
  -0.250   0.3496   0.01469   0.00859  -0.0823   0.7704   0.7425
   0.000   0.3777   0.01467   0.00852  -0.0821   0.7652   0.7515
   0.250   0.4025   0.01460   0.00846  -0.0814   0.7573   0.7575
   0.500   0.4344   0.01435   0.00812  -0.0816   0.7518   0.7639
   0.750   0.4582   0.01429   0.00806  -0.0808   0.7421   0.7708
   1.000   0.4886   0.01409   0.00781  -0.0809   0.7365   0.7765
   1.250   0.5129   0.01411   0.00785  -0.0804   0.7283   0.7839
   1.500   0.5415   0.01397   0.00770  -0.0802   0.7224   0.7898
   1.750   0.5672   0.01396   0.00769  -0.0797   0.7148   0.7974
   2.000   0.5946   0.01384   0.00756  -0.0795   0.7077   0.8044
   2.250   0.6211   0.01379   0.00752  -0.0791   0.7002   0.8118
   2.500   0.6478   0.01368   0.00741  -0.0787   0.6921   0.8195
   2.750   0.6734   0.01361   0.00736  -0.0781   0.6836   0.8280
   3.000   0.7007   0.01346   0.00720  -0.0777   0.6750   0.8363
   3.250   0.7245   0.01339   0.00717  -0.0768   0.6644   0.8458
   3.500   0.7506   0.01325   0.00702  -0.0762   0.6550   0.8548
   3.750   0.7748   0.01315   0.00695  -0.0753   0.6442   0.8655
   4.000   0.7976   0.01308   0.00693  -0.0742   0.6329   0.8772
   4.250   0.8218   0.01297   0.00686  -0.0732   0.6220   0.8897
   4.500   0.8466   0.01286   0.00675  -0.0723   0.6104   0.9043
   4.750   0.8705   0.01279   0.00676  -0.0714   0.5964   0.9228
   5.000   0.9030   0.01277   0.00677  -0.0724   0.5809   0.9471
   5.250   0.9447   0.01281   0.00681  -0.0754   0.5623   0.9872
   5.500   0.9696   0.01296   0.00692  -0.0754   0.5433   1.0000
   5.750   0.9927   0.01315   0.00703  -0.0749   0.5233   1.0000
   6.000   1.0149   0.01341   0.00718  -0.0741   0.5025   1.0000
   6.250   1.0351   0.01372   0.00740  -0.0729   0.4795   1.0000
   6.500   1.0540   0.01411   0.00766  -0.0715   0.4565   1.0000
   6.750   1.0718   0.01454   0.00799  -0.0700   0.4335   1.0000
   7.000   1.0880   0.01503   0.00835  -0.0681   0.4110   1.0000
   7.250   1.1035   0.01556   0.00876  -0.0662   0.3901   1.0000
   7.500   1.1184   0.01608   0.00921  -0.0642   0.3704   1.0000
   7.750   1.1316   0.01662   0.00967  -0.0619   0.3527   1.0000
   8.000   1.1437   0.01720   0.01017  -0.0595   0.3364   1.0000
   8.250   1.1556   0.01782   0.01071  -0.0571   0.3209   1.0000
   8.500   1.1679   0.01847   0.01130  -0.0548   0.3068   1.0000
   8.750   1.1805   0.01917   0.01193  -0.0528   0.2938   1.0000
   9.000   1.1928   0.01991   0.01261  -0.0507   0.2814   1.0000
   9.250   1.2054   0.02064   0.01331  -0.0488   0.2694   1.0000
   9.500   1.2183   0.02135   0.01404  -0.0470   0.2581   1.0000
   9.750   1.2309   0.02215   0.01481  -0.0452   0.2478   1.0000
  10.000   1.2425   0.02298   0.01559  -0.0434   0.2377   1.0000
  10.250   1.2546   0.02376   0.01645  -0.0417   0.2277   1.0000
  10.500   1.2659   0.02466   0.01732  -0.0400   0.2188   1.0000
  10.750   1.2767   0.02556   0.01825  -0.0383   0.2098   1.0000
  11.000   1.2879   0.02651   0.01923  -0.0368   0.2012   1.0000
  11.250   1.2978   0.02756   0.02025  -0.0352   0.1933   1.0000
  11.500   1.3085   0.02858   0.02137  -0.0338   0.1852   1.0000
  11.750   1.3175   0.02978   0.02249  -0.0323   0.1777   1.0000
  12.000   1.3272   0.03090   0.02375  -0.0309   0.1701   1.0000
  12.250   1.3350   0.03224   0.02501  -0.0295   0.1629   1.0000
  12.500   1.3427   0.03352   0.02645  -0.0283   0.1553   1.0000
  12.750   1.3487   0.03505   0.02788  -0.0270   0.1482   1.0000
  13.000   1.3545   0.03652   0.02955  -0.0258   0.1404   1.0000
  13.250   1.3591   0.03824   0.03119  -0.0246   0.1340   1.0000
  13.500   1.3645   0.03989   0.03302  -0.0238   0.1267   1.0000
  13.750   1.3672   0.04185   0.03491  -0.0227   0.1207   1.0000
  14.000   1.3727   0.04368   0.03691  -0.0220   0.1143   1.0000
  14.250   1.3749   0.04583   0.03905  -0.0213   0.1089   1.0000
  14.500   1.3787   0.04795   0.04127  -0.0207   0.1034   1.0000
  14.750   1.3809   0.05025   0.04366  -0.0203   0.0981   1.0000
  15.000   1.3819   0.05275   0.04613  -0.0198   0.0939   1.0000
  15.250   1.3851   0.05516   0.04872  -0.0196   0.0892   1.0000
  15.500   1.3854   0.05790   0.05150  -0.0196   0.0851   1.0000
  15.750   1.3846   0.06081   0.05443  -0.0196   0.0812   1.0000
  16.000   1.3860   0.06366   0.05745  -0.0198   0.0773   1.0000
  16.250   1.3855   0.06677   0.06063  -0.0202   0.0742   1.0000
  16.500   1.3829   0.07008   0.06392  -0.0206   0.0712   1.0000
  16.750   1.3834   0.07324   0.06724  -0.0211   0.0687   1.0000
  17.000   1.3827   0.07662   0.07077  -0.0218   0.0662   1.0000
  17.250   1.3810   0.08020   0.07447  -0.0227   0.0639   1.0000
  17.500   1.3781   0.08392   0.07822  -0.0237   0.0618   1.0000
  17.750   1.3753   0.08766   0.08202  -0.0247   0.0594   1.0000
  18.000   1.3712   0.09192   0.08647  -0.0263   0.0574   1.0000
  18.250   1.3663   0.09634   0.09104  -0.0280   0.0551   1.0000
  18.500   1.3612   0.10083   0.09563  -0.0299   0.0532   1.0000
  18.750   1.3558   0.10527   0.10008  -0.0318   0.0512   1.0000
  19.000   1.3493   0.11008   0.10503  -0.0340   0.0492   1.0000
  19.250   1.3425   0.11513   0.11026  -0.0364   0.0475   1.0000
<< Back to HQ 3.0/15 AIRFOIL (hq3015-il)

Polar data table (+)

Polar graphs


<< Back to HQ 3.0/15 AIRFOIL (hq3015-il)