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HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il)
Reynolds number: 500,000
Max Cl/Cd: 113.58 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3010-il-500000.txt
Download as CSV file: xf-hq3010-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.4372   0.15884   0.15632  -0.0164   1.0000   0.0101
 -13.750  -0.4311   0.15554   0.15302  -0.0176   1.0000   0.0103
  -8.000  -0.3741   0.07653   0.07452  -0.0460   0.9961   0.0190
  -7.750  -0.3560   0.06832   0.06631  -0.0595   0.9880   0.0191
  -7.500  -0.3319   0.05922   0.05704  -0.0745   0.9829   0.0192
  -7.250  -0.3144   0.05267   0.05028  -0.0821   0.9759   0.0192
  -6.250  -0.2438   0.02280   0.01849  -0.0975   0.9501   0.0134
  -6.000  -0.2194   0.02015   0.01546  -0.0975   0.9440   0.0133
  -5.750  -0.1959   0.01750   0.01241  -0.0972   0.9380   0.0133
  -5.500  -0.1724   0.01530   0.00988  -0.0965   0.9314   0.0135
  -5.250  -0.1473   0.01383   0.00825  -0.0962   0.9262   0.0147
  -5.000  -0.1221   0.01321   0.00755  -0.0957   0.9194   0.0157
  -4.750  -0.0963   0.01224   0.00643  -0.0952   0.9141   0.0161
  -4.500  -0.0711   0.01150   0.00560  -0.0946   0.9075   0.0170
  -4.250  -0.0449   0.01091   0.00491  -0.0941   0.9017   0.0184
  -4.000  -0.0192   0.01023   0.00412  -0.0937   0.8957   0.0212
  -3.750   0.0076   0.00991   0.00378  -0.0933   0.8894   0.0274
  -3.500   0.0345   0.00952   0.00341  -0.0931   0.8839   0.0466
  -3.250   0.0613   0.00931   0.00317  -0.0929   0.8771   0.0558
  -3.000   0.0888   0.00914   0.00295  -0.0927   0.8717   0.0654
  -2.750   0.1154   0.00884   0.00273  -0.0926   0.8646   0.0873
  -2.500   0.1416   0.00823   0.00245  -0.0925   0.8584   0.1888
  -2.250   0.1653   0.00715   0.00226  -0.0924   0.8506   0.4606
  -2.000   0.1916   0.00689   0.00220  -0.0921   0.8440   0.5553
  -1.750   0.2184   0.00680   0.00218  -0.0917   0.8362   0.5992
  -1.500   0.2460   0.00676   0.00212  -0.0915   0.8300   0.6281
  -1.250   0.2732   0.00672   0.00211  -0.0912   0.8226   0.6516
  -1.000   0.3005   0.00670   0.00209  -0.0909   0.8163   0.6773
  -0.750   0.3274   0.00669   0.00208  -0.0905   0.8078   0.6995
  -0.500   0.3539   0.00667   0.00208  -0.0899   0.7988   0.7246
  -0.250   0.3805   0.00667   0.00207  -0.0894   0.7890   0.7454
   0.000   0.4076   0.00667   0.00206  -0.0891   0.7801   0.7586
   0.250   0.4350   0.00667   0.00203  -0.0889   0.7725   0.7687
   0.500   0.4622   0.00666   0.00203  -0.0887   0.7634   0.7778
   0.750   0.4896   0.00667   0.00202  -0.0885   0.7544   0.7880
   1.000   0.5167   0.00668   0.00201  -0.0882   0.7447   0.7985
   1.250   0.5433   0.00667   0.00200  -0.0879   0.7330   0.8092
   1.500   0.5699   0.00667   0.00201  -0.0875   0.7211   0.8211
   1.750   0.5964   0.00667   0.00203  -0.0871   0.7100   0.8345
   2.000   0.6225   0.00666   0.00206  -0.0867   0.6985   0.8502
   2.250   0.6479   0.00665   0.00208  -0.0860   0.6862   0.8703
   2.500   0.6720   0.00658   0.00210  -0.0850   0.6730   0.9035
   2.750   0.7087   0.00654   0.00211  -0.0869   0.6569   1.0000
   3.000   0.7359   0.00667   0.00219  -0.0868   0.6399   1.0000
   3.250   0.7626   0.00681   0.00226  -0.0866   0.6211   1.0000
   3.500   0.7888   0.00697   0.00236  -0.0864   0.5981   1.0000
   3.750   0.8144   0.00717   0.00247  -0.0860   0.5724   1.0000
   4.000   0.8391   0.00743   0.00262  -0.0854   0.5407   1.0000
   4.250   0.8631   0.00775   0.00279  -0.0847   0.5051   1.0000
   4.500   0.8864   0.00813   0.00300  -0.0840   0.4670   1.0000
   4.750   0.9094   0.00855   0.00326  -0.0832   0.4270   1.0000
   5.000   0.9323   0.00899   0.00355  -0.0825   0.3891   1.0000
   5.250   0.9549   0.00946   0.00385  -0.0817   0.3509   1.0000
   5.500   0.9772   0.00996   0.00417  -0.0809   0.3124   1.0000
   5.750   0.9997   0.01044   0.00451  -0.0802   0.2803   1.0000
   6.000   1.0222   0.01092   0.00486  -0.0794   0.2502   1.0000
   6.250   1.0444   0.01143   0.00524  -0.0787   0.2186   1.0000
   6.500   1.0662   0.01196   0.00561  -0.0779   0.1891   1.0000
   6.750   1.0882   0.01247   0.00600  -0.0771   0.1641   1.0000
   7.000   1.1102   0.01296   0.00641  -0.0763   0.1438   1.0000
   7.250   1.1323   0.01344   0.00682  -0.0755   0.1246   1.0000
   7.500   1.1533   0.01400   0.00730  -0.0746   0.1039   1.0000
   7.750   1.1732   0.01464   0.00782  -0.0735   0.0811   1.0000
   8.000   1.1911   0.01544   0.00844  -0.0722   0.0562   1.0000
   8.250   1.2105   0.01609   0.00903  -0.0710   0.0423   1.0000
   8.500   1.2293   0.01676   0.00966  -0.0698   0.0313   1.0000
   8.750   1.2452   0.01767   0.01047  -0.0681   0.0172   1.0000
   9.000   1.2611   0.01853   0.01132  -0.0663   0.0101   1.0000
   9.250   1.2766   0.01938   0.01220  -0.0645   0.0078   1.0000
   9.500   1.2903   0.02022   0.01317  -0.0623   0.0071   1.0000
   9.750   1.3032   0.02104   0.01409  -0.0601   0.0067   1.0000
  10.000   1.3143   0.02196   0.01513  -0.0576   0.0064   1.0000
  10.250   1.3244   0.02295   0.01623  -0.0552   0.0062   1.0000
  10.500   1.3327   0.02407   0.01747  -0.0526   0.0060   1.0000
  10.750   1.3402   0.02527   0.01879  -0.0501   0.0060   1.0000
  11.000   1.3457   0.02665   0.02029  -0.0476   0.0058   1.0000
  11.250   1.3501   0.02815   0.02192  -0.0452   0.0058   1.0000
  11.500   1.3532   0.02984   0.02373  -0.0428   0.0058   1.0000
  11.750   1.3551   0.03170   0.02574  -0.0406   0.0057   1.0000
  12.000   1.3569   0.03366   0.02782  -0.0386   0.0056   1.0000
  12.250   1.3574   0.03585   0.03017  -0.0368   0.0056   1.0000
  12.500   1.3591   0.03797   0.03241  -0.0354   0.0054   1.0000
  12.750   1.3588   0.04042   0.03499  -0.0341   0.0053   1.0000
  13.000   1.3563   0.04322   0.03793  -0.0330   0.0052   1.0000
  13.250   1.3521   0.04632   0.04116  -0.0322   0.0050   1.0000
  13.500   1.3478   0.04962   0.04462  -0.0317   0.0050   1.0000
  13.750   1.3414   0.05334   0.04850  -0.0315   0.0049   1.0000
  14.000   1.3367   0.05701   0.05233  -0.0316   0.0050   1.0000
  14.250   1.3270   0.06156   0.05706  -0.0322   0.0049   1.0000
  14.500   1.3203   0.06592   0.06158  -0.0331   0.0049   1.0000
  14.750   1.3093   0.07115   0.06699  -0.0347   0.0049   1.0000
  15.000   1.2977   0.07680   0.07282  -0.0367   0.0048   1.0000
  15.250   1.2891   0.08227   0.07846  -0.0390   0.0049   1.0000
  15.500   1.2779   0.08842   0.08478  -0.0419   0.0049   1.0000
  15.750   1.2657   0.09512   0.09164  -0.0452   0.0049   1.0000
  16.000   1.2531   0.10216   0.09885  -0.0490   0.0049   1.0000
  16.250   1.2393   0.10971   0.10656  -0.0533   0.0049   1.0000
  16.500   1.2269   0.11729   0.11429  -0.0577   0.0050   1.0000
  16.750   1.2131   0.12542   0.12258  -0.0626   0.0050   1.0000
  17.000   1.1986   0.13407   0.13140  -0.0678   0.0051   1.0000
  17.250   1.1836   0.14300   0.14048  -0.0733   0.0051   1.0000
  17.500   1.1655   0.15325   0.15089  -0.0797   0.0052   1.0000
  17.750   1.1430   0.16533   0.16316  -0.0872   0.0053   1.0000
  18.000   1.0270   0.21869   0.21668  -0.1137   0.0083   1.0000
  18.250   1.0356   0.22062   0.21863  -0.1154   0.0079   1.0000
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