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HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.29 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1585-il-1000000.txt
Download as CSV file: xf-hq1585-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/8.5 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.7257   0.04437   0.04262  -0.0455   1.0000   0.0064
  -9.500  -0.7322   0.03976   0.03778  -0.0462   1.0000   0.0064
  -9.250  -0.7634   0.02942   0.02665  -0.0463   1.0000   0.0064
  -9.000  -0.7642   0.02363   0.02023  -0.0452   1.0000   0.0066
  -8.750  -0.7506   0.02077   0.01701  -0.0443   1.0000   0.0068
  -8.500  -0.7310   0.01940   0.01546  -0.0435   1.0000   0.0070
  -8.250  -0.7087   0.01881   0.01481  -0.0429   1.0000   0.0073
  -8.000  -0.6883   0.01765   0.01349  -0.0420   1.0000   0.0075
  -7.750  -0.6669   0.01689   0.01263  -0.0412   1.0000   0.0079
  -7.500  -0.6460   0.01627   0.01192  -0.0401   1.0000   0.0084
  -7.250  -0.6140   0.01559   0.01113  -0.0414   0.9974   0.0090
  -7.000  -0.5794   0.01527   0.01072  -0.0430   0.9934   0.0094
  -6.750  -0.5502   0.01281   0.00800  -0.0442   0.9874   0.0105
  -6.500  -0.5152   0.01238   0.00754  -0.0460   0.9830   0.0113
  -6.250  -0.4822   0.01190   0.00701  -0.0473   0.9753   0.0123
  -6.000  -0.4482   0.01144   0.00648  -0.0487   0.9674   0.0132
  -5.750  -0.4161   0.01133   0.00631  -0.0496   0.9561   0.0138
  -5.500  -0.3911   0.01005   0.00489  -0.0494   0.9413   0.0159
  -5.250  -0.3648   0.00980   0.00458  -0.0491   0.9277   0.0172
  -5.000  -0.3389   0.00950   0.00421  -0.0486   0.9152   0.0184
  -4.750  -0.3125   0.00926   0.00390  -0.0483   0.9042   0.0194
  -4.500  -0.2862   0.00896   0.00351  -0.0480   0.8944   0.0204
  -4.250  -0.2603   0.00841   0.00285  -0.0475   0.8850   0.0230
  -4.000  -0.2332   0.00817   0.00256  -0.0474   0.8765   0.0252
  -3.750  -0.2061   0.00800   0.00234  -0.0472   0.8690   0.0275
  -3.500  -0.1787   0.00774   0.00203  -0.0470   0.8613   0.0321
  -3.250  -0.1516   0.00750   0.00180  -0.0469   0.8547   0.0451
  -3.000  -0.1243   0.00723   0.00160  -0.0468   0.8477   0.0709
  -2.750  -0.0981   0.00675   0.00140  -0.0467   0.8407   0.1549
  -2.500  -0.0715   0.00634   0.00124  -0.0466   0.8325   0.2367
  -2.250  -0.0449   0.00602   0.00113  -0.0465   0.8243   0.3129
  -2.000  -0.0183   0.00566   0.00102  -0.0464   0.8162   0.4010
  -1.750   0.0084   0.00532   0.00096  -0.0463   0.8088   0.4950
  -1.500   0.0347   0.00504   0.00093  -0.0461   0.8007   0.5897
  -1.250   0.0621   0.00493   0.00092  -0.0459   0.7922   0.6308
  -1.000   0.0894   0.00488   0.00091  -0.0457   0.7840   0.6629
  -0.750   0.1172   0.00484   0.00091  -0.0455   0.7757   0.6883
  -0.500   0.1450   0.00483   0.00091  -0.0454   0.7689   0.7074
  -0.250   0.1731   0.00481   0.00092  -0.0453   0.7619   0.7253
   0.000   0.2011   0.00482   0.00092  -0.0453   0.7546   0.7368
   0.250   0.2291   0.00482   0.00092  -0.0452   0.7456   0.7473
   0.750   0.2851   0.00484   0.00094  -0.0450   0.7276   0.7677
   1.000   0.3128   0.00484   0.00096  -0.0449   0.7155   0.7793
   1.250   0.3402   0.00487   0.00096  -0.0447   0.6952   0.7896
   1.500   0.3669   0.00497   0.00096  -0.0443   0.6613   0.7996
   1.750   0.3932   0.00508   0.00099  -0.0439   0.6278   0.8099
   2.000   0.4198   0.00519   0.00104  -0.0436   0.5955   0.8207
   2.250   0.4461   0.00533   0.00111  -0.0433   0.5597   0.8320
   2.500   0.4712   0.00561   0.00120  -0.0428   0.4963   0.8442
   2.750   0.4952   0.00601   0.00136  -0.0421   0.4197   0.8590
   3.000   0.5191   0.00634   0.00152  -0.0414   0.3551   0.8814
   3.250   0.5421   0.00653   0.00167  -0.0404   0.3111   0.9263
   3.500   0.5791   0.00679   0.00183  -0.0426   0.2677   1.0000
   3.750   0.6052   0.00714   0.00200  -0.0424   0.2272   1.0000
   4.000   0.6311   0.00749   0.00219  -0.0422   0.1924   1.0000
   4.250   0.6566   0.00792   0.00242  -0.0420   0.1448   1.0000
   4.500   0.6804   0.00859   0.00277  -0.0415   0.0820   1.0000
   4.750   0.7051   0.00914   0.00312  -0.0411   0.0452   1.0000
   5.000   0.7312   0.00947   0.00341  -0.0409   0.0391   1.0000
   5.250   0.7576   0.00976   0.00374  -0.0406   0.0359   1.0000
   5.500   0.7842   0.00999   0.00399  -0.0405   0.0346   1.0000
   5.750   0.8105   0.01024   0.00426  -0.0403   0.0323   1.0000
   6.000   0.8364   0.01056   0.00457  -0.0400   0.0294   1.0000
   6.250   0.8614   0.01103   0.00511  -0.0396   0.0263   1.0000
   6.500   0.8883   0.01115   0.00523  -0.0395   0.0253   1.0000
   6.750   0.9153   0.01127   0.00534  -0.0395   0.0222   1.0000
   7.000   0.9406   0.01163   0.00559  -0.0392   0.0137   1.0000
   7.250   0.9650   0.01215   0.00608  -0.0387   0.0099   1.0000
   7.500   0.9892   0.01272   0.00672  -0.0381   0.0083   1.0000
   7.750   1.0135   0.01324   0.00729  -0.0376   0.0076   1.0000
   8.000   1.0373   0.01379   0.00791  -0.0371   0.0071   1.0000
   8.250   1.0605   0.01444   0.00863  -0.0364   0.0067   1.0000
   8.500   1.0828   0.01518   0.00945  -0.0356   0.0063   1.0000
   8.750   1.1030   0.01621   0.01060  -0.0346   0.0060   1.0000
   9.000   1.1193   0.01777   0.01235  -0.0330   0.0057   1.0000
   9.250   1.1412   0.01846   0.01313  -0.0322   0.0055   1.0000
   9.500   1.1618   0.01931   0.01409  -0.0313   0.0054   1.0000
   9.750   1.1811   0.02029   0.01519  -0.0303   0.0052   1.0000
  10.000   1.1994   0.02138   0.01641  -0.0291   0.0050   1.0000
  10.250   1.2158   0.02266   0.01783  -0.0277   0.0048   1.0000
  10.500   1.2306   0.02408   0.01941  -0.0262   0.0047   1.0000
  10.750   1.2435   0.02561   0.02110  -0.0245   0.0046   1.0000
  11.000   1.2533   0.02740   0.02309  -0.0225   0.0045   1.0000
  11.250   1.2598   0.02933   0.02522  -0.0202   0.0044   1.0000
  11.500   1.2635   0.03096   0.02702  -0.0175   0.0044   1.0000
  11.750   1.2607   0.03279   0.02903  -0.0141   0.0043   1.0000
  12.000   1.2604   0.03438   0.03074  -0.0116   0.0042   1.0000
  12.250   1.2545   0.03668   0.03320  -0.0093   0.0042   1.0000
  12.500   1.2440   0.03971   0.03644  -0.0074   0.0042   1.0000
  12.750   1.2346   0.04287   0.03977  -0.0065   0.0041   1.0000
  13.000   1.2234   0.04656   0.04363  -0.0064   0.0041   1.0000
  13.250   1.1986   0.05258   0.04990  -0.0076   0.0042   1.0000
  13.500   1.1928   0.05646   0.05388  -0.0093   0.0041   1.0000
  13.750   1.1860   0.06096   0.05848  -0.0117   0.0041   1.0000
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