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HQ 3.0/12 AIRFOIL (hq3012-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/12 AIRFOIL (hq3012-il)
Reynolds number: 50,000
Max Cl/Cd: 34.39 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3012-il-50000.txt
Download as CSV file: xf-hq3012-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3403   0.10661   0.09996  -0.0296   1.0000   0.2743
  -8.750  -0.3538   0.10574   0.09922  -0.0286   1.0000   0.2863
  -8.500  -0.3523   0.10313   0.09669  -0.0269   1.0000   0.3013
  -8.250  -0.3516   0.10064   0.09429  -0.0249   1.0000   0.3162
  -8.000  -0.3499   0.09805   0.09178  -0.0227   1.0000   0.3310
  -7.750  -0.3488   0.09556   0.08938  -0.0203   1.0000   0.3454
  -7.500  -0.3525   0.09355   0.08746  -0.0175   1.0000   0.3601
  -7.250  -0.3620   0.09211   0.08614  -0.0141   1.0000   0.3753
  -6.750  -0.3537   0.08734   0.08147  -0.0076   1.0000   0.4178
  -6.500  -0.3763   0.08711   0.08139  -0.0026   1.0000   0.4348
  -5.750  -0.5154   0.06108   0.05477  -0.0385   1.0000   0.1673
  -5.500  -0.5125   0.06916   0.06382  -0.0193   1.0000   0.2727
  -5.250  -0.4836   0.04946   0.04215  -0.0422   1.0000   0.1362
  -5.000  -0.4649   0.04547   0.03780  -0.0427   1.0000   0.1324
  -4.750  -0.4432   0.04201   0.03375  -0.0434   1.0000   0.1337
  -4.500  -0.4188   0.03899   0.02998  -0.0439   1.0000   0.1369
  -4.250  -0.3967   0.03645   0.02728  -0.0437   1.0000   0.1433
  -4.000  -0.3719   0.03447   0.02471  -0.0435   1.0000   0.1519
  -3.750  -0.3498   0.03272   0.02287  -0.0430   1.0000   0.1638
  -3.500  -0.3264   0.03112   0.02104  -0.0424   1.0000   0.1740
  -3.250  -0.3041   0.02993   0.01976  -0.0416   1.0000   0.1900
  -3.000  -0.2818   0.02883   0.01860  -0.0405   1.0000   0.2048
  -2.750  -0.2602   0.02792   0.01771  -0.0396   1.0000   0.2286
  -2.500  -0.2378   0.02690   0.01689  -0.0388   1.0000   0.2642
  -2.250  -0.2140   0.02469   0.01647  -0.0382   1.0000   0.4601
  -2.000  -0.2241   0.02503   0.01771  -0.0269   1.0000   0.7370
  -1.750  -0.2288   0.02511   0.01785  -0.0184   1.0000   0.8175
  -1.500  -0.2272   0.02487   0.01764  -0.0116   1.0000   0.8885
  -1.250  -0.1714   0.02497   0.01747  -0.0167   1.0000   1.0000
  -1.000  -0.1561   0.02491   0.01714  -0.0173   1.0000   1.0000
  -0.750  -0.1351   0.02511   0.01702  -0.0185   1.0000   1.0000
  -0.500  -0.1120   0.02547   0.01710  -0.0200   1.0000   1.0000
  -0.250  -0.0884   0.02595   0.01730  -0.0215   1.0000   1.0000
   0.000  -0.0649   0.02650   0.01760  -0.0228   1.0000   1.0000
   0.250  -0.0420   0.02713   0.01800  -0.0240   1.0000   1.0000
   0.500  -0.0197   0.02782   0.01849  -0.0250   1.0000   1.0000
   0.750   0.0296   0.02943   0.01984  -0.0310   0.9866   1.0000
   1.000   0.0749   0.03090   0.02110  -0.0361   0.9732   1.0000
   1.250   0.1163   0.03223   0.02226  -0.0403   0.9597   1.0000
   1.500   0.1557   0.03349   0.02337  -0.0440   0.9457   1.0000
   1.750   0.1944   0.03471   0.02447  -0.0474   0.9311   1.0000
   2.000   0.2333   0.03589   0.02556  -0.0508   0.9157   1.0000
   2.250   0.2737   0.03706   0.02665  -0.0541   0.8993   1.0000
   2.500   0.3169   0.03820   0.02774  -0.0576   0.8826   1.0000
   2.750   0.3489   0.03912   0.02863  -0.0593   0.8651   1.0000
   3.000   0.3807   0.04001   0.02951  -0.0608   0.8472   1.0000
   3.250   0.4152   0.04090   0.03040  -0.0626   0.8296   1.0000
   3.500   0.4528   0.04172   0.03124  -0.0646   0.8121   1.0000
   3.750   0.4939   0.04240   0.03197  -0.0668   0.7949   1.0000
   4.000   0.5243   0.04311   0.03271  -0.0675   0.7764   1.0000
   4.250   0.5533   0.04375   0.03343  -0.0679   0.7569   1.0000
   4.500   0.5926   0.04406   0.03382  -0.0692   0.7385   1.0000
   4.750   0.6409   0.04384   0.03372  -0.0709   0.7208   1.0000
   5.000   0.6613   0.04445   0.03444  -0.0698   0.6990   1.0000
   5.250   0.7057   0.04389   0.03402  -0.0705   0.6799   1.0000
   5.500   0.7605   0.04243   0.03277  -0.0716   0.6628   1.0000
   5.750   0.7857   0.04242   0.03288  -0.0702   0.6409   1.0000
   6.000   0.8388   0.04050   0.03117  -0.0705   0.6227   1.0000
   6.250   0.9036   0.03758   0.02850  -0.0713   0.6049   1.0000
   6.500   0.9393   0.03655   0.02762  -0.0702   0.5816   1.0000
   6.750   1.0015   0.03373   0.02494  -0.0709   0.5581   1.0000
   7.000   1.0428   0.03251   0.02375  -0.0703   0.5305   1.0000
   7.250   1.0752   0.03212   0.02335  -0.0692   0.5016   1.0000
   7.500   1.1035   0.03226   0.02347  -0.0680   0.4730   1.0000
   7.750   1.1282   0.03281   0.02398  -0.0666   0.4451   1.0000
   8.000   1.1504   0.03370   0.02485  -0.0652   0.4190   1.0000
   8.250   1.1743   0.03463   0.02572  -0.0640   0.3937   1.0000
   8.500   1.2009   0.03558   0.02656  -0.0632   0.3690   1.0000
   8.750   1.2138   0.03709   0.02822  -0.0610   0.3471   1.0000
   9.000   1.2391   0.03820   0.02917  -0.0602   0.3240   1.0000
   9.250   1.2501   0.03992   0.03106  -0.0579   0.3039   1.0000
   9.500   1.2733   0.04122   0.03221  -0.0569   0.2817   1.0000
   9.750   1.2841   0.04319   0.03433  -0.0547   0.2634   1.0000
  10.000   1.2937   0.04518   0.03651  -0.0524   0.2457   1.0000
  10.250   1.3048   0.04734   0.03879  -0.0504   0.2295   1.0000
  10.500   1.3144   0.04950   0.04107  -0.0483   0.2144   1.0000
  10.750   1.3206   0.05201   0.04374  -0.0460   0.2019   1.0000
  11.000   1.3299   0.05476   0.04663  -0.0442   0.1911   1.0000
  11.250   1.3441   0.05716   0.04903  -0.0428   0.1793   1.0000
  11.500   1.3220   0.06082   0.05318  -0.0385   0.1757   1.0000
  11.750   1.3413   0.06352   0.05585  -0.0378   0.1655   1.0000
  12.000   1.3131   0.06744   0.06015  -0.0336   0.1645   1.0000
  12.250   1.2822   0.07178   0.06477  -0.0301   0.1640   1.0000
  12.500   1.2485   0.07695   0.07017  -0.0281   0.1642   1.0000
  12.750   1.2127   0.08315   0.07655  -0.0276   0.1649   1.0000
  13.000   1.1758   0.09057   0.08408  -0.0287   0.1658   1.0000
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