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HQ 3.0/11 AIRFOIL (hq3011-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/11 AIRFOIL (hq3011-il)
Reynolds number: 100,000
Max Cl/Cd: 58.5 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3011-il-100000.txt
Download as CSV file: xf-hq3011-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/11 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3609   0.09508   0.09042  -0.0403   1.0000   0.0971
  -8.500  -0.3806   0.09290   0.08839  -0.0418   1.0000   0.1001
  -8.250  -0.4076   0.09141   0.08706  -0.0415   1.0000   0.1008
  -8.000  -0.4373   0.09011   0.08590  -0.0395   1.0000   0.1010
  -7.750  -0.4662   0.08773   0.08360  -0.0407   1.0000   0.1012
  -7.500  -0.4929   0.08561   0.08144  -0.0414   1.0000   0.1015
  -7.250  -0.4506   0.08262   0.07861  -0.0303   1.0000   0.1065
  -7.000  -0.4635   0.08029   0.07635  -0.0294   1.0000   0.1083
  -6.750  -0.4770   0.07738   0.07348  -0.0299   1.0000   0.1103
  -6.500  -0.5109   0.07365   0.06940  -0.0382   1.0000   0.1156
  -6.250  -0.5043   0.06931   0.06527  -0.0351   1.0000   0.1177
  -6.000  -0.4975   0.06750   0.06356  -0.0315   1.0000   0.1224
  -5.750  -0.5006   0.06333   0.05920  -0.0346   1.0000   0.1325
  -5.500  -0.4931   0.06121   0.05713  -0.0327   1.0000   0.1398
  -5.250  -0.4870   0.05799   0.05381  -0.0330   1.0000   0.1506
  -5.000  -0.4681   0.05438   0.04983  -0.0380   0.9975   0.1745
  -4.750  -0.4127   0.03994   0.03388  -0.0462   0.9953   0.0784
  -4.500  -0.3724   0.03395   0.02683  -0.0487   0.9921   0.0641
  -4.250  -0.3349   0.03059   0.02272  -0.0506   0.9879   0.0632
  -4.000  -0.2967   0.02901   0.02082  -0.0530   0.9836   0.0698
  -3.750  -0.2611   0.02695   0.01822  -0.0541   0.9790   0.0746
  -3.500  -0.2258   0.02577   0.01682  -0.0556   0.9737   0.0873
  -3.250  -0.1881   0.02425   0.01537  -0.0579   0.9699   0.1054
  -3.000  -0.1582   0.02337   0.01453  -0.0586   0.9637   0.1231
  -2.750  -0.1230   0.02264   0.01383  -0.0601   0.9583   0.1432
  -2.500  -0.0882   0.02189   0.01328  -0.0617   0.9531   0.1734
  -2.250  -0.0637   0.01973   0.01302  -0.0621   0.9473   0.5106
  -2.000  -0.0370   0.01991   0.01360  -0.0602   0.9415   0.7019
  -1.750  -0.0201   0.02008   0.01385  -0.0573   0.9329   0.7580
  -1.500   0.0093   0.02039   0.01416  -0.0563   0.9270   0.8091
  -1.250   0.0243   0.02052   0.01426  -0.0533   0.9179   0.8491
  -1.000   0.0536   0.02054   0.01429  -0.0521   0.9125   0.9056
  -0.500   0.1650   0.02065   0.01415  -0.0636   0.9001   1.0000
  -0.250   0.1916   0.02080   0.01413  -0.0649   0.8904   1.0000
   0.000   0.2391   0.02091   0.01407  -0.0693   0.8848   1.0000
   0.250   0.2653   0.02116   0.01419  -0.0701   0.8746   1.0000
   0.500   0.3159   0.02120   0.01410  -0.0745   0.8698   1.0000
   0.750   0.3400   0.02149   0.01429  -0.0745   0.8589   1.0000
   1.000   0.3753   0.02163   0.01435  -0.0761   0.8503   1.0000
   1.250   0.4240   0.02139   0.01405  -0.0795   0.8428   1.0000
   1.500   0.4581   0.02133   0.01394  -0.0804   0.8317   1.0000
   1.750   0.5112   0.02074   0.01333  -0.0840   0.8266   1.0000
   2.000   0.5375   0.02081   0.01337  -0.0836   0.8148   1.0000
   2.250   0.5671   0.02079   0.01336  -0.0836   0.8040   1.0000
   2.500   0.6125   0.02019   0.01277  -0.0857   0.7983   1.0000
   2.750   0.6399   0.02012   0.01270  -0.0851   0.7862   1.0000
   3.000   0.6700   0.01990   0.01253  -0.0849   0.7745   1.0000
   3.250   0.7024   0.01953   0.01219  -0.0848   0.7630   1.0000
   3.500   0.7371   0.01901   0.01168  -0.0848   0.7518   1.0000
   3.750   0.7716   0.01845   0.01115  -0.0848   0.7400   1.0000
   4.000   0.8013   0.01811   0.01086  -0.0842   0.7255   1.0000
   4.250   0.8283   0.01789   0.01068  -0.0832   0.7087   1.0000
   4.500   0.8561   0.01763   0.01045  -0.0823   0.6909   1.0000
   4.750   0.8854   0.01730   0.01016  -0.0816   0.6721   1.0000
   5.000   0.9115   0.01714   0.01002  -0.0805   0.6499   1.0000
   5.250   0.9386   0.01695   0.00980  -0.0795   0.6256   1.0000
   5.500   0.9626   0.01692   0.00976  -0.0781   0.5967   1.0000
   5.750   0.9849   0.01701   0.00984  -0.0766   0.5633   1.0000
   6.000   1.0074   0.01722   0.00992  -0.0751   0.5279   1.0000
   6.250   1.0277   0.01764   0.01019  -0.0734   0.4897   1.0000
   6.500   1.0479   0.01822   0.01057  -0.0718   0.4535   1.0000
   6.750   1.0667   0.01893   0.01115  -0.0702   0.4184   1.0000
   7.000   1.0854   0.01971   0.01177  -0.0686   0.3867   1.0000
   7.250   1.1038   0.02052   0.01246  -0.0671   0.3574   1.0000
   7.500   1.1216   0.02136   0.01320  -0.0656   0.3302   1.0000
   7.750   1.1390   0.02224   0.01399  -0.0640   0.3050   1.0000
   8.000   1.1566   0.02319   0.01481  -0.0626   0.2820   1.0000
   8.250   1.1725   0.02409   0.01577  -0.0609   0.2592   1.0000
   8.500   1.1884   0.02508   0.01669  -0.0592   0.2383   1.0000
   8.750   1.2020   0.02603   0.01767  -0.0573   0.2172   1.0000
   9.000   1.2159   0.02713   0.01866  -0.0554   0.1978   1.0000
   9.250   1.2271   0.02826   0.01988  -0.0532   0.1778   1.0000
   9.500   1.2379   0.02950   0.02106  -0.0510   0.1597   1.0000
   9.750   1.2507   0.03099   0.02243  -0.0492   0.1434   1.0000
  10.000   1.2647   0.03258   0.02403  -0.0475   0.1293   1.0000
  10.250   1.2733   0.03386   0.02542  -0.0451   0.1179   1.0000
  10.500   1.2803   0.03524   0.02694  -0.0426   0.1076   1.0000
  10.750   1.2893   0.03681   0.02861  -0.0406   0.0984   1.0000
  11.000   1.2955   0.03830   0.03001  -0.0385   0.0895   1.0000
  11.250   1.2945   0.03964   0.03161  -0.0357   0.0820   1.0000
  11.500   1.2944   0.04140   0.03346  -0.0334   0.0741   1.0000
  11.750   1.2938   0.04317   0.03520  -0.0315   0.0668   1.0000
  12.000   1.2896   0.04552   0.03783  -0.0294   0.0591   1.0000
  12.250   1.2881   0.04842   0.04078  -0.0277   0.0519   1.0000
  12.500   1.2851   0.05133   0.04381  -0.0261   0.0457   1.0000
  12.750   1.2876   0.05520   0.04788  -0.0248   0.0415   1.0000
  13.000   1.2850   0.05878   0.05180  -0.0236   0.0391   1.0000
  13.250   1.2806   0.06244   0.05570  -0.0227   0.0371   1.0000
  13.500   1.2763   0.06617   0.05961  -0.0222   0.0357   1.0000
  13.750   1.2717   0.07018   0.06379  -0.0220   0.0348   1.0000
  14.000   1.2643   0.07496   0.06874  -0.0221   0.0339   1.0000
  14.250   1.2495   0.08058   0.07462  -0.0228   0.0335   1.0000
  14.500   1.2316   0.08636   0.08066  -0.0242   0.0334   1.0000
  14.750   1.2114   0.09262   0.08717  -0.0265   0.0334   1.0000
  15.000   1.1922   0.09882   0.09362  -0.0295   0.0336   1.0000
  15.250   1.1684   0.10625   0.10134  -0.0340   0.0341   1.0000
  15.500   1.0924   0.12703   0.12267  -0.0493   0.0386   1.0000
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