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HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il)
Reynolds number: 50,000
Max Cl/Cd: 34.95 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2012-il-50000-n5.txt
Download as CSV file: xf-hq2012-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/12 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4914   0.09066   0.08354  -0.0461   1.0000   0.0493
 -10.250  -0.4997   0.08473   0.07766  -0.0494   1.0000   0.0491
 -10.000  -0.5137   0.07864   0.07161  -0.0532   1.0000   0.0489
  -9.750  -0.5291   0.07345   0.06643  -0.0561   1.0000   0.0486
  -9.500  -0.5495   0.06894   0.06192  -0.0578   1.0000   0.0484
  -9.250  -0.5699   0.06524   0.05819  -0.0575   1.0000   0.0482
  -9.000  -0.5868   0.06154   0.05438  -0.0567   1.0000   0.0481
  -8.750  -0.6010   0.05798   0.05064  -0.0553   1.0000   0.0482
  -8.500  -0.6120   0.05451   0.04692  -0.0534   1.0000   0.0485
  -8.250  -0.6200   0.05120   0.04327  -0.0512   1.0000   0.0490
  -8.000  -0.6213   0.04841   0.04030  -0.0490   1.0000   0.0503
  -7.750  -0.6166   0.04663   0.03849  -0.0470   1.0000   0.0525
  -7.500  -0.6120   0.04461   0.03628  -0.0448   1.0000   0.0549
  -7.250  -0.6071   0.04213   0.03345  -0.0427   1.0000   0.0573
  -7.000  -0.5992   0.03950   0.03035  -0.0406   1.0000   0.0596
  -6.750  -0.5886   0.03725   0.02774  -0.0387   1.0000   0.0631
  -6.500  -0.5758   0.03583   0.02622  -0.0371   1.0000   0.0674
  -6.250  -0.5607   0.03401   0.02407  -0.0354   1.0000   0.0720
  -6.000  -0.5450   0.03248   0.02234  -0.0339   1.0000   0.0777
  -5.750  -0.5286   0.03128   0.02102  -0.0325   1.0000   0.0845
  -5.500  -0.5113   0.03006   0.01967  -0.0310   1.0000   0.0919
  -5.250  -0.4892   0.02902   0.01843  -0.0303   0.9984   0.1015
  -5.000  -0.4575   0.02790   0.01729  -0.0314   0.9927   0.1130
  -4.750  -0.4264   0.02693   0.01623  -0.0325   0.9865   0.1287
  -4.500  -0.3957   0.02596   0.01526  -0.0336   0.9805   0.1473
  -4.250  -0.3656   0.02501   0.01443  -0.0350   0.9740   0.1779
  -4.000  -0.3352   0.02389   0.01357  -0.0366   0.9679   0.2309
  -3.750  -0.3093   0.02260   0.01294  -0.0375   0.9610   0.3325
  -3.500  -0.2849   0.02210   0.01329  -0.0366   0.9546   0.5023
  -3.250  -0.2612   0.02231   0.01362  -0.0351   0.9467   0.5946
  -3.000  -0.2342   0.02266   0.01390  -0.0341   0.9399   0.6549
  -2.750  -0.2115   0.02295   0.01409  -0.0322   0.9321   0.6978
  -2.500  -0.1849   0.02322   0.01424  -0.0312   0.9256   0.7345
  -2.250  -0.1621   0.02337   0.01429  -0.0295   0.9178   0.7631
  -2.000  -0.1327   0.02349   0.01427  -0.0291   0.9119   0.7893
  -1.750  -0.1115   0.02355   0.01426  -0.0272   0.9037   0.8158
  -1.500  -0.0792   0.02362   0.01423  -0.0272   0.8985   0.8442
  -1.250  -0.0552   0.02362   0.01414  -0.0263   0.8902   0.8664
  -1.000  -0.0150   0.02363   0.01399  -0.0288   0.8849   0.8810
  -0.750   0.0175   0.02365   0.01391  -0.0300   0.8772   0.8952
  -0.500   0.0617   0.02369   0.01383  -0.0334   0.8716   0.9080
  -0.250   0.1043   0.02375   0.01380  -0.0367   0.8651   0.9210
   0.000   0.1489   0.02381   0.01379  -0.0403   0.8583   0.9342
   0.250   0.1984   0.02383   0.01373  -0.0448   0.8528   0.9467
   0.500   0.2415   0.02392   0.01378  -0.0485   0.8443   0.9613
   0.750   0.2927   0.02389   0.01371  -0.0533   0.8386   0.9741
   1.000   0.3344   0.02397   0.01379  -0.0568   0.8291   0.9923
   1.250   0.3550   0.02408   0.01388  -0.0564   0.8189   1.0000
   1.500   0.3802   0.02408   0.01384  -0.0564   0.8105   1.0000
   1.750   0.3943   0.02425   0.01397  -0.0545   0.7979   1.0000
   2.000   0.4166   0.02428   0.01397  -0.0536   0.7849   1.0000
   2.250   0.4436   0.02416   0.01384  -0.0532   0.7709   1.0000
   2.500   0.4714   0.02399   0.01365  -0.0527   0.7563   1.0000
   2.750   0.4985   0.02387   0.01352  -0.0521   0.7421   1.0000
   3.000   0.5246   0.02387   0.01355  -0.0515   0.7290   1.0000
   3.250   0.5513   0.02386   0.01357  -0.0510   0.7160   1.0000
   3.500   0.5781   0.02384   0.01358  -0.0504   0.7025   1.0000
   3.750   0.6046   0.02381   0.01360  -0.0497   0.6882   1.0000
   4.000   0.6304   0.02379   0.01367  -0.0489   0.6729   1.0000
   4.250   0.6558   0.02378   0.01372  -0.0480   0.6565   1.0000
   4.500   0.6817   0.02373   0.01374  -0.0471   0.6389   1.0000
   4.750   0.7087   0.02364   0.01373  -0.0463   0.6206   1.0000
   5.000   0.7310   0.02374   0.01391  -0.0450   0.5985   1.0000
   5.250   0.7573   0.02367   0.01388  -0.0440   0.5763   1.0000
   5.500   0.7799   0.02379   0.01406  -0.0426   0.5500   1.0000
   5.750   0.8035   0.02391   0.01422  -0.0414   0.5222   1.0000
   6.000   0.8269   0.02411   0.01439  -0.0401   0.4931   1.0000
   6.250   0.8494   0.02444   0.01465  -0.0388   0.4634   1.0000
   6.500   0.8706   0.02491   0.01503  -0.0375   0.4343   1.0000
   6.750   0.8906   0.02551   0.01558  -0.0361   0.4064   1.0000
   7.000   0.9095   0.02621   0.01619  -0.0347   0.3802   1.0000
   7.250   0.9275   0.02697   0.01687  -0.0332   0.3553   1.0000
   7.500   0.9438   0.02781   0.01768  -0.0317   0.3308   1.0000
   7.750   0.9592   0.02870   0.01856  -0.0301   0.3076   1.0000
   8.000   0.9738   0.02966   0.01946  -0.0284   0.2853   1.0000
   8.250   0.9873   0.03069   0.02049  -0.0267   0.2637   1.0000
   8.500   0.9997   0.03178   0.02158  -0.0250   0.2427   1.0000
   8.750   1.0107   0.03293   0.02274  -0.0232   0.2226   1.0000
   9.000   1.0193   0.03411   0.02400  -0.0211   0.2027   1.0000
   9.250   1.0272   0.03538   0.02529  -0.0190   0.1846   1.0000
   9.500   1.0342   0.03676   0.02668  -0.0171   0.1682   1.0000
   9.750   1.0429   0.03827   0.02819  -0.0154   0.1535   1.0000
  10.000   1.0530   0.03985   0.02982  -0.0140   0.1412   1.0000
  10.250   1.0634   0.04153   0.03158  -0.0126   0.1298   1.0000
  10.500   1.0733   0.04330   0.03343  -0.0114   0.1201   1.0000
  10.750   1.0831   0.04505   0.03511  -0.0102   0.1129   1.0000
  11.000   1.0972   0.04704   0.03738  -0.0093   0.1062   1.0000
  11.250   1.1109   0.04887   0.03920  -0.0084   0.1010   1.0000
  11.500   1.1203   0.05124   0.04191  -0.0074   0.0959   1.0000
  11.750   1.1265   0.05352   0.04438  -0.0064   0.0913   1.0000
  12.000   1.1385   0.05552   0.04629  -0.0057   0.0871   1.0000
  12.250   1.1394   0.05874   0.04995  -0.0048   0.0845   1.0000
  12.500   1.1371   0.06215   0.05370  -0.0042   0.0820   1.0000
  12.750   1.1331   0.06559   0.05738  -0.0038   0.0795   1.0000
  13.000   1.1318   0.06867   0.06059  -0.0036   0.0769   1.0000
  13.250   1.1348   0.07164   0.06358  -0.0034   0.0742   1.0000
  13.500   1.1152   0.07697   0.06925  -0.0045   0.0733   1.0000
  13.750   1.0924   0.08316   0.07575  -0.0065   0.0728   1.0000
  14.000   1.0658   0.09049   0.08332  -0.0097   0.0727   1.0000
  14.250   1.0349   0.09932   0.09236  -0.0144   0.0729   1.0000
  14.500   1.0000   0.11014   0.10334  -0.0208   0.0735   1.0000
  14.750   0.9623   0.12330   0.11656  -0.0288   0.0741   1.0000
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