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HQ 3.5/14 AIRFOIL (hq3514-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/14 AIRFOIL (hq3514-il)
Reynolds number: 100,000
Max Cl/Cd: 54.42 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3514-il-100000-n5.txt
Download as CSV file: xf-hq3514-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/14 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3768   0.09642   0.09152  -0.0547   1.0000   0.0388
 -10.500  -0.3909   0.09291   0.08811  -0.0543   1.0000   0.0393
 -10.000  -0.5209   0.05886   0.05375  -0.0825   0.9802   0.0364
  -9.750  -0.5128   0.05552   0.05030  -0.0869   0.9718   0.0372
  -9.500  -0.5023   0.05271   0.04735  -0.0897   0.9628   0.0381
  -9.250  -0.4954   0.04914   0.04352  -0.0924   0.9539   0.0391
  -9.000  -0.4833   0.04534   0.03932  -0.0954   0.9471   0.0408
  -8.750  -0.4778   0.04159   0.03504  -0.0961   0.9376   0.0427
  -8.500  -0.4622   0.03751   0.03020  -0.0978   0.9318   0.0447
  -8.250  -0.4443   0.03608   0.02871  -0.0975   0.9240   0.0460
  -8.000  -0.4184   0.03483   0.02731  -0.0986   0.9190   0.0484
  -7.750  -0.3938   0.03301   0.02514  -0.0993   0.9142   0.0509
  -7.500  -0.3743   0.03122   0.02294  -0.0987   0.9071   0.0528
  -7.250  -0.3465   0.02962   0.02108  -0.0995   0.9032   0.0554
  -7.000  -0.3211   0.02865   0.02005  -0.0997   0.8981   0.0579
  -6.750  -0.2966   0.02758   0.01880  -0.0995   0.8922   0.0603
  -6.500  -0.2666   0.02649   0.01745  -0.1001   0.8885   0.0637
  -6.250  -0.2388   0.02544   0.01627  -0.1004   0.8845   0.0669
  -6.000  -0.2163   0.02469   0.01552  -0.0998   0.8784   0.0697
  -5.750  -0.1876   0.02390   0.01465  -0.1001   0.8746   0.0735
  -5.500  -0.1561   0.02324   0.01378  -0.1008   0.8717   0.0784
  -5.250  -0.1366   0.02255   0.01319  -0.0997   0.8648   0.0822
  -5.000  -0.1100   0.02195   0.01255  -0.0996   0.8604   0.0874
  -4.750  -0.0806   0.02137   0.01189  -0.1000   0.8573   0.0940
  -4.500  -0.0594   0.02090   0.01146  -0.0991   0.8515   0.1004
  -4.250  -0.0348   0.02050   0.01099  -0.0987   0.8461   0.1084
  -4.000  -0.0060   0.01988   0.01039  -0.0991   0.8422   0.1207
  -3.750   0.0163   0.01946   0.01007  -0.0984   0.8360   0.1363
  -3.500   0.0406   0.01894   0.00978  -0.0981   0.8303   0.1809
  -3.250   0.0686   0.01806   0.00929  -0.0987   0.8264   0.2751
  -3.000   0.0854   0.01741   0.00948  -0.0971   0.8194   0.4551
  -2.750   0.1111   0.01737   0.00951  -0.0964   0.8140   0.5326
  -2.500   0.1401   0.01736   0.00951  -0.0961   0.8105   0.5757
  -2.250   0.1609   0.01757   0.00974  -0.0945   0.8037   0.6040
  -2.000   0.1870   0.01767   0.00980  -0.0938   0.7984   0.6295
  -1.750   0.2173   0.01766   0.00971  -0.0937   0.7946   0.6502
  -1.500   0.2373   0.01788   0.00991  -0.0920   0.7869   0.6697
  -1.250   0.2640   0.01795   0.00993  -0.0914   0.7821   0.6887
  -1.000   0.2936   0.01791   0.00984  -0.0912   0.7788   0.7035
  -0.750   0.3132   0.01810   0.01003  -0.0896   0.7716   0.7139
  -0.500   0.3410   0.01809   0.00995  -0.0895   0.7669   0.7240
  -0.250   0.3719   0.01796   0.00978  -0.0897   0.7633   0.7325
   0.000   0.3928   0.01808   0.00989  -0.0885   0.7553   0.7413
   0.250   0.4222   0.01794   0.00970  -0.0884   0.7497   0.7496
   0.500   0.4480   0.01790   0.00963  -0.0880   0.7428   0.7578
   0.750   0.4745   0.01782   0.00954  -0.0875   0.7356   0.7656
   1.000   0.5052   0.01766   0.00933  -0.0878   0.7300   0.7732
   1.250   0.5278   0.01770   0.00939  -0.0868   0.7212   0.7806
   1.500   0.5604   0.01750   0.00913  -0.0873   0.7156   0.7886
   1.750   0.5812   0.01761   0.00929  -0.0860   0.7063   0.7972
   2.000   0.6116   0.01747   0.00913  -0.0863   0.7005   0.8062
   2.250   0.6336   0.01755   0.00927  -0.0852   0.6912   0.8164
   2.500   0.6637   0.01736   0.00907  -0.0852   0.6840   0.8259
   2.750   0.6849   0.01743   0.00920  -0.0840   0.6732   0.8373
   3.000   0.7118   0.01733   0.00913  -0.0836   0.6646   0.8493
   3.250   0.7354   0.01731   0.00917  -0.0826   0.6546   0.8628
   3.500   0.7587   0.01730   0.00925  -0.0816   0.6443   0.8795
   3.750   0.7871   0.01717   0.00917  -0.0815   0.6338   0.9009
   4.000   0.8191   0.01707   0.00913  -0.0822   0.6199   0.9370
   4.250   0.8493   0.01706   0.00911  -0.0828   0.6036   1.0000
   4.500   0.8726   0.01720   0.00924  -0.0822   0.5854   1.0000
   4.750   0.8961   0.01735   0.00936  -0.0816   0.5668   1.0000
   5.000   0.9197   0.01750   0.00944  -0.0809   0.5466   1.0000
   5.250   0.9433   0.01767   0.00953  -0.0802   0.5255   1.0000
   5.500   0.9659   0.01792   0.00970  -0.0793   0.5043   1.0000
   5.750   0.9885   0.01821   0.00987  -0.0785   0.4844   1.0000
   6.000   1.0105   0.01857   0.01010  -0.0775   0.4654   1.0000
   6.250   1.0315   0.01901   0.01044  -0.0765   0.4474   1.0000
   6.500   1.0516   0.01949   0.01085  -0.0754   0.4300   1.0000
   6.750   1.0706   0.02000   0.01132  -0.0741   0.4127   1.0000
   7.000   1.0881   0.02053   0.01185  -0.0727   0.3948   1.0000
   7.250   1.1035   0.02106   0.01239  -0.0709   0.3761   1.0000
   7.500   1.1180   0.02161   0.01294  -0.0690   0.3573   1.0000
   7.750   1.1317   0.02223   0.01350  -0.0670   0.3401   1.0000
   8.000   1.1448   0.02293   0.01411  -0.0650   0.3248   1.0000
   8.250   1.1580   0.02370   0.01481  -0.0631   0.3106   1.0000
   8.500   1.1718   0.02449   0.01557  -0.0614   0.2974   1.0000
   8.750   1.1857   0.02533   0.01638  -0.0598   0.2849   1.0000
   9.000   1.1994   0.02621   0.01722  -0.0582   0.2736   1.0000
   9.250   1.2137   0.02705   0.01815  -0.0568   0.2620   1.0000
   9.500   1.2275   0.02794   0.01909  -0.0553   0.2512   1.0000
   9.750   1.2400   0.02891   0.02004  -0.0538   0.2415   1.0000
  10.000   1.2536   0.02982   0.02106  -0.0524   0.2316   1.0000
  10.250   1.2668   0.03081   0.02209  -0.0511   0.2235   1.0000
  10.500   1.2792   0.03183   0.02319  -0.0497   0.2154   1.0000
  10.750   1.2907   0.03290   0.02432  -0.0483   0.2072   1.0000
  11.000   1.2999   0.03410   0.02553  -0.0468   0.1994   1.0000
  11.250   1.3097   0.03531   0.02683  -0.0455   0.1910   1.0000
  11.500   1.3165   0.03672   0.02818  -0.0440   0.1836   1.0000
  11.750   1.3250   0.03809   0.02972  -0.0428   0.1754   1.0000
  12.000   1.3314   0.03964   0.03123  -0.0415   0.1688   1.0000
  12.250   1.3403   0.04111   0.03287  -0.0405   0.1620   1.0000
  12.500   1.3471   0.04273   0.03454  -0.0394   0.1563   1.0000
  12.750   1.3548   0.04436   0.03630  -0.0384   0.1506   1.0000
  13.000   1.3609   0.04614   0.03823  -0.0375   0.1446   1.0000
  13.250   1.3651   0.04807   0.04018  -0.0366   0.1394   1.0000
  13.500   1.3697   0.05009   0.04248  -0.0358   0.1329   1.0000
  13.750   1.3706   0.05242   0.04490  -0.0352   0.1269   1.0000
  14.000   1.3719   0.05486   0.04754  -0.0347   0.1200   1.0000
  14.250   1.3693   0.05774   0.05053  -0.0344   0.1130   1.0000
  14.500   1.3673   0.06077   0.05374  -0.0343   0.1048   1.0000
  14.750   1.3612   0.06438   0.05741  -0.0346   0.0970   1.0000
  15.000   1.3547   0.06827   0.06142  -0.0351   0.0883   1.0000
  15.250   1.3474   0.07245   0.06571  -0.0359   0.0800   1.0000
  15.500   1.3373   0.07720   0.07052  -0.0370   0.0734   1.0000
  15.750   1.3268   0.08223   0.07564  -0.0384   0.0674   1.0000
  16.000   1.3153   0.08762   0.08112  -0.0402   0.0628   1.0000
  16.250   1.3031   0.09332   0.08693  -0.0423   0.0586   1.0000
  16.500   1.2885   0.09961   0.09329  -0.0448   0.0559   1.0000
  16.750   1.2770   0.10553   0.09935  -0.0473   0.0528   1.0000
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