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HQ 1.5/10 AIRFOIL (hq1510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/10 AIRFOIL (hq1510-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.08 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1510-il-1000000.txt
Download as CSV file: xf-hq1510-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.7197   0.04556   0.04373  -0.0529   1.0000   0.0053
 -10.250  -0.7825   0.03712   0.03487  -0.0522   1.0000   0.0051
 -10.000  -0.8000   0.03208   0.02944  -0.0502   1.0000   0.0051
  -9.750  -0.7995   0.02895   0.02600  -0.0484   1.0000   0.0052
  -9.500  -0.7940   0.02628   0.02305  -0.0465   1.0000   0.0054
  -9.250  -0.7831   0.02437   0.02091  -0.0448   1.0000   0.0056
  -9.000  -0.7725   0.02234   0.01863  -0.0429   1.0000   0.0057
  -8.750  -0.7581   0.02116   0.01727  -0.0411   1.0000   0.0060
  -8.500  -0.7399   0.01981   0.01574  -0.0400   0.9994   0.0061
  -8.250  -0.7081   0.01855   0.01430  -0.0416   0.9969   0.0064
  -8.000  -0.6746   0.01779   0.01341  -0.0433   0.9942   0.0065
  -7.750  -0.6449   0.01632   0.01175  -0.0444   0.9901   0.0066
  -7.500  -0.6165   0.01392   0.00905  -0.0456   0.9859   0.0070
  -7.250  -0.5836   0.01272   0.00773  -0.0472   0.9831   0.0074
  -7.000  -0.5527   0.01209   0.00703  -0.0482   0.9771   0.0078
  -6.750  -0.5200   0.01158   0.00647  -0.0495   0.9714   0.0085
  -6.500  -0.4898   0.01102   0.00584  -0.0501   0.9630   0.0093
  -6.250  -0.4605   0.01059   0.00533  -0.0505   0.9534   0.0098
  -5.750  -0.4101   0.00946   0.00400  -0.0495   0.9281   0.0125
  -5.500  -0.3842   0.00919   0.00365  -0.0491   0.9165   0.0143
  -5.250  -0.3587   0.00880   0.00324  -0.0486   0.9057   0.0200
  -5.000  -0.3325   0.00857   0.00301  -0.0482   0.8961   0.0297
  -4.750  -0.3061   0.00835   0.00279  -0.0479   0.8865   0.0381
  -4.500  -0.2791   0.00821   0.00261  -0.0478   0.8776   0.0425
  -4.250  -0.2524   0.00802   0.00240  -0.0475   0.8693   0.0504
  -4.000  -0.2254   0.00784   0.00221  -0.0474   0.8607   0.0601
  -3.750  -0.1986   0.00764   0.00204  -0.0472   0.8528   0.0752
  -3.500  -0.1720   0.00738   0.00186  -0.0470   0.8446   0.1063
  -3.250  -0.1457   0.00701   0.00167  -0.0469   0.8364   0.1600
  -3.000  -0.1195   0.00668   0.00151  -0.0467   0.8283   0.2229
  -2.750  -0.0932   0.00628   0.00135  -0.0466   0.8197   0.2963
  -2.500  -0.0680   0.00576   0.00120  -0.0463   0.8120   0.4161
  -2.250  -0.0414   0.00548   0.00111  -0.0462   0.8035   0.4877
  -2.000  -0.0143   0.00532   0.00106  -0.0460   0.7940   0.5345
  -1.750   0.0130   0.00524   0.00101  -0.0458   0.7840   0.5683
  -1.500   0.0405   0.00517   0.00098  -0.0457   0.7741   0.6007
  -1.250   0.0681   0.00512   0.00096  -0.0456   0.7648   0.6257
  -1.000   0.0960   0.00512   0.00094  -0.0455   0.7561   0.6409
  -0.750   0.1237   0.00509   0.00094  -0.0454   0.7466   0.6628
  -0.500   0.1514   0.00508   0.00094  -0.0452   0.7368   0.6830
  -0.250   0.1792   0.00509   0.00094  -0.0451   0.7275   0.6954
   0.000   0.2071   0.00509   0.00094  -0.0451   0.7170   0.7065
   0.250   0.2350   0.00510   0.00095  -0.0450   0.7067   0.7175
   1.000   0.3183   0.00517   0.00101  -0.0447   0.6754   0.7517
   1.250   0.3462   0.00520   0.00104  -0.0447   0.6639   0.7607
   1.500   0.3739   0.00524   0.00107  -0.0446   0.6514   0.7697
   1.750   0.4014   0.00528   0.00111  -0.0444   0.6370   0.7783
   2.000   0.4289   0.00534   0.00115  -0.0443   0.6206   0.7875
   2.250   0.4560   0.00542   0.00121  -0.0441   0.6009   0.7974
   2.500   0.4826   0.00552   0.00126  -0.0438   0.5747   0.8074
   2.750   0.5088   0.00567   0.00134  -0.0435   0.5401   0.8183
   3.000   0.5340   0.00591   0.00144  -0.0430   0.4926   0.8304
   3.250   0.5579   0.00628   0.00160  -0.0424   0.4285   0.8439
   3.500   0.5819   0.00661   0.00177  -0.0417   0.3728   0.8595
   3.750   0.6057   0.00689   0.00193  -0.0410   0.3255   0.8799
   4.000   0.6286   0.00710   0.00211  -0.0400   0.2886   0.9130
   4.250   0.6634   0.00730   0.00231  -0.0416   0.2616   0.9733
   4.500   0.6961   0.00757   0.00249  -0.0429   0.2386   1.0000
   4.750   0.7219   0.00784   0.00266  -0.0426   0.2164   1.0000
   5.000   0.7475   0.00812   0.00285  -0.0423   0.1943   1.0000
   5.250   0.7729   0.00842   0.00306  -0.0420   0.1692   1.0000
   5.500   0.7971   0.00886   0.00333  -0.0416   0.1333   1.0000
   5.750   0.8204   0.00940   0.00367  -0.0410   0.0967   1.0000
   6.000   0.8442   0.00988   0.00401  -0.0404   0.0710   1.0000
   6.250   0.8685   0.01029   0.00435  -0.0400   0.0557   1.0000
   6.500   0.8933   0.01065   0.00466  -0.0396   0.0460   1.0000
   6.750   0.9178   0.01104   0.00501  -0.0391   0.0381   1.0000
   7.000   0.9433   0.01130   0.00529  -0.0388   0.0352   1.0000
   7.250   0.9678   0.01167   0.00563  -0.0383   0.0305   1.0000
   7.500   0.9926   0.01199   0.00597  -0.0379   0.0274   1.0000
   7.750   1.0176   0.01227   0.00628  -0.0376   0.0246   1.0000
   8.000   1.0413   0.01269   0.00666  -0.0371   0.0197   1.0000
   8.250   1.0646   0.01315   0.00706  -0.0365   0.0132   1.0000
   8.500   1.0856   0.01388   0.00773  -0.0355   0.0066   1.0000
   8.750   1.1078   0.01446   0.00837  -0.0346   0.0055   1.0000
   9.000   1.1301   0.01498   0.00896  -0.0339   0.0052   1.0000
   9.250   1.1517   0.01557   0.00961  -0.0330   0.0048   1.0000
   9.500   1.1723   0.01624   0.01035  -0.0320   0.0044   1.0000
   9.750   1.1921   0.01697   0.01116  -0.0309   0.0042   1.0000
  10.000   1.2104   0.01780   0.01208  -0.0296   0.0040   1.0000
  10.250   1.2267   0.01878   0.01319  -0.0281   0.0039   1.0000
  10.500   1.2394   0.02002   0.01458  -0.0260   0.0037   1.0000
  10.750   1.2523   0.02113   0.01581  -0.0241   0.0037   1.0000
  11.000   1.2650   0.02216   0.01695  -0.0221   0.0037   1.0000
  11.250   1.2765   0.02305   0.01794  -0.0199   0.0036   1.0000
  11.500   1.2853   0.02395   0.01893  -0.0174   0.0036   1.0000
  11.750   1.2915   0.02504   0.02015  -0.0146   0.0035   1.0000
  12.000   1.2958   0.02631   0.02154  -0.0119   0.0035   1.0000
  12.250   1.3004   0.02762   0.02296  -0.0096   0.0034   1.0000
  12.500   1.3044   0.02904   0.02450  -0.0075   0.0034   1.0000
  12.750   1.3037   0.03095   0.02655  -0.0054   0.0033   1.0000
  13.000   1.3028   0.03300   0.02873  -0.0036   0.0033   1.0000
  13.250   1.3013   0.03523   0.03110  -0.0023   0.0033   1.0000
  13.500   1.3012   0.03747   0.03346  -0.0013   0.0031   1.0000
  13.750   1.3001   0.03995   0.03607  -0.0007   0.0031   1.0000
  14.000   1.2904   0.04357   0.03986  -0.0005   0.0031   1.0000
  14.250   1.2872   0.04669   0.04308  -0.0008   0.0030   1.0000
  14.500   1.2762   0.05103   0.04758  -0.0017   0.0029   1.0000
  14.750   1.2607   0.05635   0.05309  -0.0034   0.0030   1.0000
  15.000   1.2531   0.06094   0.05779  -0.0054   0.0030   1.0000
  15.250   1.2304   0.06841   0.06547  -0.0090   0.0031   1.0000
  15.500   1.2169   0.07494   0.07213  -0.0127   0.0030   1.0000
  15.750   1.1996   0.08265   0.08000  -0.0172   0.0030   1.0000
  16.000   1.1740   0.09252   0.09005  -0.0230   0.0031   1.0000
  16.250   1.1522   0.10204   0.09971  -0.0286   0.0031   1.0000
  16.500   1.1323   0.11133   0.10912  -0.0340   0.0031   1.0000
  16.750   1.1011   0.12347   0.12142  -0.0409   0.0032   1.0000
  17.000   1.0851   0.13240   0.13043  -0.0461   0.0031   1.0000
  17.250   1.0579   0.14446   0.14262  -0.0530   0.0033   1.0000
  17.500   1.0334   0.15656   0.15482  -0.0598   0.0033   1.0000
  17.750   0.9965   0.17314   0.17154  -0.0689   0.0035   1.0000
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