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HQ 1.5/8.5 AIRFOIL (hq1585-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/8.5 AIRFOIL (hq1585-il)
Reynolds number: 50,000
Max Cl/Cd: 35.64 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1585-il-50000-n5.txt
Download as CSV file: xf-hq1585-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5432   0.09249   0.08561  -0.0261   1.0000   0.0489
  -9.000  -0.5422   0.08775   0.08092  -0.0283   1.0000   0.0486
  -8.750  -0.5430   0.08288   0.07610  -0.0306   1.0000   0.0482
  -8.500  -0.5458   0.07843   0.07169  -0.0330   1.0000   0.0477
  -8.250  -0.5499   0.07372   0.06700  -0.0357   1.0000   0.0472
  -8.000  -0.5533   0.06896   0.06218  -0.0381   1.0000   0.0468
  -7.750  -0.5557   0.06414   0.05724  -0.0402   1.0000   0.0464
  -7.500  -0.5555   0.05946   0.05236  -0.0418   1.0000   0.0462
  -7.250  -0.5522   0.05486   0.04748  -0.0428   1.0000   0.0460
  -7.000  -0.5455   0.05047   0.04272  -0.0434   1.0000   0.0461
  -6.750  -0.5354   0.04639   0.03820  -0.0434   1.0000   0.0466
  -6.500  -0.5226   0.04284   0.03393  -0.0431   1.0000   0.0487
  -6.250  -0.5081   0.03978   0.03080  -0.0427   1.0000   0.0517
  -6.000  -0.4909   0.03707   0.02777  -0.0419   1.0000   0.0538
  -5.750  -0.4720   0.03432   0.02458  -0.0410   1.0000   0.0552
  -5.500  -0.4517   0.03189   0.02173  -0.0398   1.0000   0.0570
  -5.250  -0.4305   0.02980   0.01924  -0.0386   1.0000   0.0595
  -5.000  -0.4100   0.02809   0.01732  -0.0374   1.0000   0.0646
  -4.750  -0.3897   0.02671   0.01575  -0.0362   1.0000   0.0706
  -4.500  -0.3686   0.02537   0.01414  -0.0345   1.0000   0.0745
  -4.250  -0.3494   0.02407   0.01285  -0.0330   1.0000   0.0793
  -4.000  -0.3299   0.02303   0.01166  -0.0314   1.0000   0.0868
  -3.750  -0.3104   0.02204   0.01067  -0.0303   1.0000   0.1027
  -3.500  -0.2903   0.02093   0.00967  -0.0295   1.0000   0.1265
  -3.250  -0.2705   0.01938   0.00875  -0.0291   1.0000   0.2161
  -3.000  -0.2549   0.01777   0.00837  -0.0275   1.0000   0.4500
  -2.750  -0.2432   0.01737   0.00857  -0.0235   1.0000   0.6144
  -2.500  -0.2348   0.01735   0.00880  -0.0184   1.0000   0.7283
  -2.250  -0.2272   0.01725   0.00880  -0.0130   1.0000   0.8099
  -2.000  -0.2103   0.01708   0.00859  -0.0099   1.0000   0.8640
  -1.750  -0.1760   0.01696   0.00828  -0.0108   1.0000   0.9151
  -1.500  -0.1234   0.01685   0.00786  -0.0161   1.0000   0.9814
  -1.250  -0.1040   0.01681   0.00757  -0.0162   1.0000   1.0000
  -1.000  -0.0727   0.01695   0.00746  -0.0183   0.9942   1.0000
  -0.750  -0.0349   0.01718   0.00741  -0.0213   0.9861   1.0000
  -0.500   0.0020   0.01742   0.00744  -0.0241   0.9776   1.0000
  -0.250   0.0385   0.01767   0.00752  -0.0267   0.9688   1.0000
   0.000   0.0759   0.01794   0.00764  -0.0294   0.9602   1.0000
   0.250   0.1150   0.01823   0.00781  -0.0323   0.9514   1.0000
   0.500   0.1512   0.01848   0.00798  -0.0345   0.9407   1.0000
   0.750   0.1891   0.01873   0.00818  -0.0370   0.9302   1.0000
   1.000   0.2293   0.01897   0.00840  -0.0397   0.9200   1.0000
   1.250   0.2700   0.01919   0.00863  -0.0425   0.9098   1.0000
   1.500   0.3073   0.01936   0.00885  -0.0443   0.8968   1.0000
   1.750   0.3452   0.01947   0.00901  -0.0461   0.8824   1.0000
   2.000   0.3822   0.01953   0.00914  -0.0474   0.8674   1.0000
   2.250   0.4144   0.01960   0.00932  -0.0479   0.8509   1.0000
   2.500   0.4454   0.01964   0.00946  -0.0479   0.8332   1.0000
   2.750   0.4771   0.01963   0.00955  -0.0478   0.8149   1.0000
   3.000   0.5088   0.01958   0.00966  -0.0476   0.7969   1.0000
   3.250   0.5342   0.01967   0.00988  -0.0466   0.7755   1.0000
   3.500   0.5625   0.01965   0.01000  -0.0457   0.7549   1.0000
   3.750   0.5868   0.01971   0.01022  -0.0444   0.7296   1.0000
   4.000   0.6115   0.01970   0.01043  -0.0429   0.7017   1.0000
   4.250   0.6365   0.01964   0.01050  -0.0413   0.6691   1.0000
   4.500   0.6612   0.01957   0.01051  -0.0395   0.6286   1.0000
   4.750   0.6847   0.01963   0.01058  -0.0376   0.5778   1.0000
   5.000   0.7074   0.01987   0.01073  -0.0356   0.5192   1.0000
   5.250   0.7274   0.02041   0.01102  -0.0334   0.4481   1.0000
   5.500   0.7435   0.02139   0.01149  -0.0313   0.3648   1.0000
   5.750   0.7592   0.02257   0.01223  -0.0297   0.2902   1.0000
   6.000   0.7769   0.02374   0.01318  -0.0285   0.2290   1.0000
   6.250   0.7946   0.02509   0.01432  -0.0274   0.1735   1.0000
   6.500   0.8122   0.02667   0.01567  -0.0263   0.1354   1.0000
   6.750   0.8316   0.02829   0.01726  -0.0252   0.1148   1.0000
   7.000   0.8526   0.02992   0.01894  -0.0241   0.1022   1.0000
   7.250   0.8737   0.03150   0.02068  -0.0233   0.0903   1.0000
   7.500   0.8956   0.03330   0.02248  -0.0224   0.0823   1.0000
   7.750   0.9202   0.03535   0.02487  -0.0216   0.0746   1.0000
   8.000   0.9390   0.03727   0.02698  -0.0207   0.0642   1.0000
   8.250   0.9567   0.03952   0.02946  -0.0197   0.0555   1.0000
   8.500   0.9740   0.04209   0.03209  -0.0189   0.0497   1.0000
   8.750   0.9885   0.04548   0.03610  -0.0175   0.0450   1.0000
   9.000   0.9992   0.04844   0.03945  -0.0163   0.0408   1.0000
   9.250   1.0079   0.05152   0.04274  -0.0152   0.0382   1.0000
   9.500   1.0128   0.05560   0.04717  -0.0140   0.0369   1.0000
   9.750   1.0104   0.05986   0.05182  -0.0126   0.0363   1.0000
  10.000   1.0024   0.06397   0.05635  -0.0111   0.0360   1.0000
  10.250   0.9890   0.06792   0.06060  -0.0097   0.0359   1.0000
  10.500   0.9726   0.07208   0.06499  -0.0091   0.0359   1.0000
  10.750   0.9546   0.07681   0.06992  -0.0100   0.0360   1.0000
  11.000   0.9367   0.08213   0.07538  -0.0121   0.0361   1.0000
  11.250   0.9178   0.08835   0.08173  -0.0156   0.0363   1.0000
  11.500   0.9006   0.09528   0.08865  -0.0199   0.0365   1.0000
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