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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 200,000
Max Cl/Cd: 73.71 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2010-il-200000.txt
Download as CSV file: xf-hq2010-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/10 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4458   0.08740   0.08397  -0.0337   1.0000   0.0482
  -8.750  -0.4511   0.08274   0.07937  -0.0372   1.0000   0.0496
  -8.500  -0.4645   0.07672   0.07344  -0.0438   1.0000   0.0506
  -8.250  -0.4829   0.07180   0.06852  -0.0482   1.0000   0.0508
  -8.000  -0.5039   0.06805   0.06461  -0.0507   1.0000   0.0515
  -7.750  -0.5147   0.06540   0.06181  -0.0500   1.0000   0.0517
  -7.500  -0.4998   0.04943   0.04623  -0.0454   1.0000   0.0529
  -7.250  -0.5043   0.04672   0.04359  -0.0426   1.0000   0.0536
  -7.000  -0.5107   0.04431   0.04117  -0.0401   1.0000   0.0542
  -6.750  -0.5125   0.04173   0.03856  -0.0383   0.9997   0.0552
  -6.500  -0.4909   0.03679   0.03344  -0.0421   0.9953   0.0577
  -6.250  -0.4690   0.03162   0.02784  -0.0459   0.9900   0.0620
  -6.000  -0.4951   0.03177   0.02609  -0.0419   0.9940   0.0290
  -5.750  -0.4667   0.02699   0.02073  -0.0436   0.9897   0.0295
  -5.500  -0.4344   0.02415   0.01760  -0.0457   0.9858   0.0318
  -5.250  -0.3978   0.02178   0.01486  -0.0475   0.9829   0.0327
  -5.000  -0.3650   0.02001   0.01285  -0.0485   0.9780   0.0347
  -4.750  -0.3290   0.01858   0.01119  -0.0499   0.9736   0.0380
  -4.500  -0.2915   0.01719   0.00977  -0.0521   0.9702   0.0464
  -4.250  -0.2592   0.01591   0.00843  -0.0530   0.9649   0.0564
  -4.000  -0.2244   0.01514   0.00768  -0.0547   0.9598   0.0741
  -3.750  -0.1861   0.01436   0.00695  -0.0572   0.9565   0.0957
  -3.500  -0.1544   0.01359   0.00632  -0.0583   0.9508   0.1266
  -3.250  -0.1245   0.01190   0.00570  -0.0600   0.9455   0.3433
  -3.000  -0.0905   0.01112   0.00574  -0.0613   0.9422   0.5772
  -2.750  -0.0618   0.01109   0.00578  -0.0612   0.9355   0.6370
  -2.500  -0.0285   0.01107   0.00579  -0.0618   0.9306   0.6801
  -2.250   0.0077   0.01106   0.00574  -0.0630   0.9272   0.7141
  -2.000   0.0329   0.01110   0.00579  -0.0621   0.9190   0.7371
  -1.750   0.0651   0.01108   0.00577  -0.0623   0.9145   0.7629
  -1.500   0.0904   0.01113   0.00581  -0.0613   0.9071   0.7862
  -1.250   0.1197   0.01105   0.00572  -0.0610   0.9012   0.8039
  -1.000   0.1453   0.01100   0.00567  -0.0600   0.8933   0.8208
  -0.750   0.1727   0.01088   0.00554  -0.0593   0.8864   0.8392
  -0.500   0.1962   0.01080   0.00546  -0.0579   0.8773   0.8563
  -0.250   0.2239   0.01062   0.00525  -0.0571   0.8700   0.8702
   0.000   0.2479   0.01048   0.00510  -0.0559   0.8591   0.8834
   0.250   0.2726   0.01035   0.00497  -0.0547   0.8488   0.8978
   0.500   0.2995   0.01020   0.00481  -0.0540   0.8398   0.9127
   0.750   0.3293   0.01006   0.00466  -0.0538   0.8298   0.9284
   1.000   0.3636   0.00996   0.00456  -0.0549   0.8189   0.9453
   1.250   0.4034   0.00987   0.00446  -0.0571   0.8092   0.9616
   1.500   0.4462   0.00976   0.00432  -0.0601   0.8004   0.9775
   1.750   0.4897   0.00968   0.00425  -0.0635   0.7891   0.9954
   2.000   0.5123   0.00968   0.00423  -0.0629   0.7772   1.0000
   2.250   0.5352   0.00970   0.00421  -0.0621   0.7655   1.0000
   2.500   0.5604   0.00972   0.00419  -0.0615   0.7533   1.0000
   2.750   0.5862   0.00974   0.00419  -0.0610   0.7400   1.0000
   3.000   0.6121   0.00978   0.00422  -0.0605   0.7255   1.0000
   3.250   0.6380   0.00982   0.00425  -0.0599   0.7092   1.0000
   3.500   0.6637   0.00987   0.00427  -0.0593   0.6913   1.0000
   3.750   0.6893   0.00993   0.00431  -0.0586   0.6711   1.0000
   4.000   0.7145   0.01002   0.00438  -0.0579   0.6468   1.0000
   4.250   0.7388   0.01015   0.00445  -0.0569   0.6163   1.0000
   4.500   0.7622   0.01034   0.00453  -0.0558   0.5761   1.0000
   4.750   0.7840   0.01066   0.00465  -0.0545   0.5231   1.0000
   5.000   0.8043   0.01116   0.00487  -0.0531   0.4574   1.0000
   5.250   0.8235   0.01183   0.00523  -0.0517   0.3989   1.0000
   5.500   0.8442   0.01246   0.00565  -0.0506   0.3543   1.0000
   5.750   0.8657   0.01305   0.00609  -0.0496   0.3209   1.0000
   6.000   0.8874   0.01363   0.00656  -0.0487   0.2924   1.0000
   6.250   0.9089   0.01422   0.00706  -0.0479   0.2654   1.0000
   6.500   0.9305   0.01479   0.00759  -0.0470   0.2376   1.0000
   6.750   0.9523   0.01533   0.00809  -0.0462   0.2034   1.0000
   7.000   0.9709   0.01617   0.00869  -0.0450   0.1502   1.0000
   7.250   0.9865   0.01740   0.00962  -0.0434   0.1089   1.0000
   7.500   1.0030   0.01855   0.01064  -0.0418   0.0913   1.0000
   7.750   1.0208   0.01957   0.01167  -0.0403   0.0810   1.0000
   8.000   1.0377   0.02069   0.01282  -0.0388   0.0731   1.0000
   8.250   1.0562   0.02158   0.01373  -0.0377   0.0658   1.0000
   8.500   1.0744   0.02253   0.01476  -0.0364   0.0593   1.0000
   8.750   1.0913   0.02346   0.01568  -0.0352   0.0527   1.0000
   9.000   1.1096   0.02429   0.01666  -0.0340   0.0471   1.0000
   9.250   1.1231   0.02546   0.01782  -0.0325   0.0404   1.0000
   9.500   1.1398   0.02618   0.01872  -0.0310   0.0330   1.0000
   9.750   1.1469   0.02807   0.02071  -0.0283   0.0262   1.0000
  10.000   1.1550   0.02949   0.02220  -0.0259   0.0223   1.0000
  10.250   1.1627   0.03226   0.02510  -0.0236   0.0204   1.0000
  10.500   1.1743   0.03416   0.02722  -0.0217   0.0194   1.0000
  10.750   1.1841   0.03641   0.02971  -0.0198   0.0184   1.0000
  11.000   1.1914   0.03882   0.03236  -0.0179   0.0178   1.0000
  11.250   1.1949   0.04134   0.03514  -0.0157   0.0173   1.0000
  11.500   1.1952   0.04398   0.03803  -0.0137   0.0169   1.0000
  11.750   1.1942   0.04613   0.04034  -0.0119   0.0162   1.0000
  12.000   1.1921   0.04850   0.04285  -0.0106   0.0156   1.0000
  12.250   1.1880   0.05128   0.04576  -0.0095   0.0151   1.0000
  12.500   1.1764   0.05535   0.05004  -0.0088   0.0147   1.0000
  12.750   1.1643   0.05952   0.05446  -0.0085   0.0147   1.0000
  13.000   1.1475   0.06448   0.05967  -0.0091   0.0146   1.0000
  13.250   1.1281   0.07010   0.06553  -0.0106   0.0145   1.0000
  13.500   1.1171   0.07480   0.07044  -0.0124   0.0147   1.0000
  13.750   1.0983   0.08114   0.07697  -0.0155   0.0146   1.0000
  14.000   1.0798   0.08804   0.08408  -0.0195   0.0147   1.0000
  14.250   1.0618   0.09562   0.09187  -0.0244   0.0149   1.0000
  14.500   0.9526   0.13022   0.12704  -0.0475   0.0194   1.0000
  14.750   0.9244   0.14455   0.14133  -0.0554   0.0203   1.0000
  15.000   0.9093   0.15486   0.15161  -0.0603   0.0209   1.0000
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