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HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il)
Reynolds number: 500,000
Max Cl/Cd: 68.24 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1010-il-500000-n5.txt
Download as CSV file: xf-hq1010-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.8185   0.05615   0.05361  -0.0366   1.0000   0.0041
 -11.750  -0.8409   0.04873   0.04600  -0.0424   1.0000   0.0041
 -11.500  -0.8574   0.04376   0.04085  -0.0451   1.0000   0.0040
 -11.250  -0.8743   0.03976   0.03665  -0.0459   1.0000   0.0040
 -11.000  -0.8928   0.03644   0.03309  -0.0440   1.0000   0.0041
 -10.750  -0.9006   0.03356   0.02994  -0.0418   1.0000   0.0041
 -10.500  -0.9003   0.03080   0.02688  -0.0400   1.0000   0.0042
 -10.250  -0.8939   0.02843   0.02422  -0.0385   1.0000   0.0042
 -10.000  -0.8833   0.02640   0.02191  -0.0371   1.0000   0.0044
  -9.750  -0.8699   0.02464   0.01991  -0.0359   1.0000   0.0044
  -9.500  -0.8532   0.02327   0.01833  -0.0348   1.0000   0.0045
  -9.250  -0.8380   0.02161   0.01642  -0.0335   1.0000   0.0047
  -9.000  -0.8231   0.01989   0.01451  -0.0321   1.0000   0.0050
  -8.750  -0.8038   0.01893   0.01343  -0.0311   1.0000   0.0053
  -8.500  -0.7838   0.01812   0.01254  -0.0301   1.0000   0.0055
  -8.250  -0.7638   0.01733   0.01164  -0.0290   1.0000   0.0058
  -8.000  -0.7440   0.01657   0.01079  -0.0279   1.0000   0.0061
  -7.750  -0.7210   0.01582   0.00993  -0.0273   0.9984   0.0065
  -7.500  -0.6901   0.01509   0.00909  -0.0285   0.9917   0.0071
  -7.250  -0.6583   0.01431   0.00819  -0.0298   0.9857   0.0080
  -7.000  -0.6270   0.01365   0.00748  -0.0310   0.9782   0.0091
  -6.750  -0.5941   0.01308   0.00683  -0.0323   0.9711   0.0102
  -6.500  -0.5629   0.01256   0.00622  -0.0333   0.9612   0.0112
  -6.250  -0.5321   0.01199   0.00558  -0.0341   0.9504   0.0133
  -6.000  -0.5020   0.01156   0.00513  -0.0348   0.9382   0.0168
  -5.750  -0.4736   0.01116   0.00471  -0.0351   0.9248   0.0228
  -5.500  -0.4462   0.01088   0.00436  -0.0350   0.9123   0.0278
  -5.250  -0.4198   0.01060   0.00405  -0.0348   0.9005   0.0338
  -5.000  -0.3935   0.01038   0.00377  -0.0345   0.8892   0.0392
  -4.750  -0.3674   0.01014   0.00351  -0.0342   0.8785   0.0473
  -4.500  -0.3413   0.00990   0.00325  -0.0339   0.8689   0.0566
  -4.000  -0.2888   0.00941   0.00277  -0.0334   0.8507   0.0863
  -3.750  -0.2625   0.00915   0.00255  -0.0331   0.8423   0.1080
  -3.500  -0.2364   0.00887   0.00234  -0.0329   0.8338   0.1402
  -3.250  -0.2101   0.00857   0.00215  -0.0327   0.8256   0.1819
  -2.500  -0.1326   0.00750   0.00163  -0.0321   0.8007   0.3660
  -2.250  -0.1074   0.00709   0.00149  -0.0317   0.7917   0.4556
  -2.000  -0.0807   0.00691   0.00142  -0.0315   0.7829   0.5017
  -1.750  -0.0544   0.00674   0.00138  -0.0312   0.7746   0.5534
  -1.500  -0.0276   0.00662   0.00136  -0.0309   0.7660   0.5964
  -1.250  -0.0005   0.00656   0.00134  -0.0307   0.7565   0.6239
  -1.000   0.0267   0.00654   0.00131  -0.0304   0.7450   0.6421
  -0.750   0.0541   0.00654   0.00128  -0.0302   0.7328   0.6560
  -0.500   0.0816   0.00653   0.00126  -0.0301   0.7210   0.6703
  -0.250   0.1090   0.00653   0.00125  -0.0299   0.7092   0.6839
   0.000   0.1365   0.00654   0.00125  -0.0297   0.6972   0.6966
   0.250   0.1638   0.00656   0.00126  -0.0295   0.6837   0.7097
   0.500   0.1911   0.00658   0.00127  -0.0293   0.6704   0.7226
   0.750   0.2186   0.00661   0.00129  -0.0292   0.6581   0.7335
   1.000   0.2461   0.00664   0.00131  -0.0290   0.6458   0.7419
   1.250   0.2736   0.00668   0.00135  -0.0289   0.6323   0.7503
   1.500   0.3009   0.00673   0.00139  -0.0287   0.6170   0.7593
   1.750   0.3281   0.00679   0.00143  -0.0285   0.5993   0.7678
   2.000   0.3549   0.00688   0.00148  -0.0283   0.5774   0.7769
   2.250   0.3813   0.00701   0.00155  -0.0279   0.5475   0.7863
   2.500   0.4071   0.00718   0.00163  -0.0275   0.5109   0.7958
   2.750   0.4326   0.00740   0.00174  -0.0271   0.4704   0.8059
   3.000   0.4575   0.00770   0.00188  -0.0266   0.4211   0.8166
   3.250   0.4812   0.00810   0.00208  -0.0259   0.3566   0.8278
   3.500   0.5056   0.00844   0.00227  -0.0254   0.3086   0.8399
   3.750   0.5305   0.00870   0.00246  -0.0249   0.2775   0.8532
   4.000   0.5553   0.00893   0.00266  -0.0244   0.2522   0.8686
   4.500   0.6057   0.00931   0.00308  -0.0233   0.2090   0.9149
   4.750   0.6396   0.00956   0.00331  -0.0248   0.1870   0.9531
   5.000   0.6769   0.00992   0.00357  -0.0271   0.1564   0.9966
   5.250   0.7016   0.01036   0.00386  -0.0268   0.1242   1.0000
   5.500   0.7254   0.01081   0.00420  -0.0263   0.0975   1.0000
   5.750   0.7496   0.01123   0.00454  -0.0259   0.0793   1.0000
   6.000   0.7741   0.01162   0.00487  -0.0254   0.0662   1.0000
   6.250   0.7983   0.01203   0.00523  -0.0250   0.0534   1.0000
   6.500   0.8224   0.01246   0.00561  -0.0245   0.0419   1.0000
   6.750   0.8465   0.01288   0.00603  -0.0240   0.0332   1.0000
   7.000   0.8707   0.01327   0.00643  -0.0235   0.0271   1.0000
   7.250   0.8943   0.01375   0.00689  -0.0230   0.0210   1.0000
   7.500   0.9177   0.01423   0.00737  -0.0224   0.0163   1.0000
   7.750   0.9408   0.01475   0.00791  -0.0218   0.0122   1.0000
   8.000   0.9630   0.01537   0.00854  -0.0210   0.0090   1.0000
   8.250   0.9854   0.01594   0.00915  -0.0203   0.0068   1.0000
   8.500   1.0068   0.01663   0.00991  -0.0195   0.0058   1.0000
   8.750   1.0285   0.01725   0.01062  -0.0187   0.0052   1.0000
   9.000   1.0496   0.01793   0.01138  -0.0178   0.0048   1.0000
   9.250   1.0701   0.01864   0.01218  -0.0169   0.0045   1.0000
   9.500   1.0894   0.01946   0.01308  -0.0158   0.0042   1.0000
   9.750   1.1076   0.02035   0.01407  -0.0147   0.0039   1.0000
  10.000   1.1237   0.02140   0.01525  -0.0133   0.0038   1.0000
  10.250   1.1359   0.02278   0.01677  -0.0114   0.0036   1.0000
  10.500   1.1502   0.02384   0.01796  -0.0098   0.0035   1.0000
  10.750   1.1624   0.02500   0.01929  -0.0080   0.0034   1.0000
  11.000   1.1713   0.02620   0.02063  -0.0057   0.0033   1.0000
  11.250   1.1763   0.02752   0.02209  -0.0030   0.0033   1.0000
  11.500   1.1798   0.02897   0.02370  -0.0004   0.0032   1.0000
  11.750   1.1822   0.03058   0.02546   0.0019   0.0032   1.0000
  12.000   1.1826   0.03246   0.02750   0.0039   0.0031   1.0000
  12.250   1.1821   0.03452   0.02972   0.0056   0.0031   1.0000
  12.500   1.1801   0.03686   0.03223   0.0069   0.0031   1.0000
  12.750   1.1749   0.03969   0.03525   0.0078   0.0030   1.0000
  13.000   1.1748   0.04215   0.03785   0.0081   0.0030   1.0000
  13.250   1.1683   0.04552   0.04139   0.0079   0.0030   1.0000
  13.500   1.1613   0.04925   0.04528   0.0072   0.0028   1.0000
  13.750   1.1527   0.05346   0.04966   0.0058   0.0029   1.0000
  14.000   1.1350   0.05944   0.05585   0.0032   0.0029   1.0000
  14.250   1.1198   0.06565   0.06224  -0.0001   0.0029   1.0000
  14.500   1.1044   0.07247   0.06922  -0.0041   0.0029   1.0000
  14.750   1.0838   0.08095   0.07788  -0.0093   0.0029   1.0000
  15.000   1.0638   0.08996   0.08706  -0.0148   0.0029   1.0000
  15.250   1.0427   0.09952   0.09675  -0.0205   0.0030   1.0000
  15.500   1.0121   0.11143   0.10882  -0.0273   0.0031   1.0000
  15.750   0.9893   0.12193   0.11944  -0.0332   0.0031   1.0000
  16.000   0.9642   0.13349   0.13110  -0.0395   0.0032   1.0000
  16.250   0.9385   0.14581   0.14352  -0.0460   0.0033   1.0000
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