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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 200,000
Max Cl/Cd: 80.82 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3510-il-200000-n5.txt
Download as CSV file: xf-hq3510-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2631   0.10354   0.10033  -0.0402   1.0000   0.0207
 -10.000  -0.2669   0.10083   0.09766  -0.0395   1.0000   0.0207
  -8.500  -0.3419   0.09214   0.08889  -0.0428   0.9980   0.0198
  -8.000  -0.3268   0.07977   0.07653  -0.0503   0.9877   0.0128
  -7.750  -0.3158   0.07524   0.07202  -0.0554   0.9809   0.0124
  -7.500  -0.3013   0.06882   0.06561  -0.0645   0.9734   0.0123
  -7.250  -0.2850   0.06208   0.05884  -0.0752   0.9642   0.0119
  -7.000  -0.2635   0.05436   0.05095  -0.0866   0.9579   0.0117
  -6.750  -0.2472   0.04764   0.04400  -0.0933   0.9488   0.0116
  -6.500  -0.2269   0.04116   0.03718  -0.0984   0.9417   0.0120
  -6.250  -0.2050   0.03499   0.03053  -0.1015   0.9347   0.0128
  -6.000  -0.1814   0.03015   0.02513  -0.1035   0.9290   0.0131
  -5.750  -0.1585   0.02632   0.02077  -0.1043   0.9225   0.0130
  -5.500  -0.1302   0.02314   0.01704  -0.1054   0.9185   0.0131
  -5.250  -0.1059   0.02063   0.01406  -0.1053   0.9122   0.0133
  -5.000  -0.0785   0.01859   0.01167  -0.1055   0.9074   0.0139
  -4.750  -0.0489   0.01727   0.01016  -0.1060   0.9039   0.0146
  -4.500  -0.0238   0.01648   0.00925  -0.1056   0.8972   0.0157
  -4.250   0.0048   0.01584   0.00849  -0.1058   0.8925   0.0179
  -4.000   0.0325   0.01499   0.00749  -0.1057   0.8877   0.0191
  -3.750   0.0586   0.01420   0.00659  -0.1054   0.8815   0.0202
  -3.500   0.0872   0.01352   0.00584  -0.1056   0.8770   0.0231
  -3.250   0.1140   0.01308   0.00529  -0.1053   0.8708   0.0293
  -3.000   0.1419   0.01267   0.00486  -0.1053   0.8654   0.0426
  -2.750   0.1702   0.01238   0.00459  -0.1055   0.8605   0.0611
  -2.500   0.1970   0.01214   0.00434  -0.1054   0.8540   0.0809
  -2.250   0.2254   0.01174   0.00404  -0.1056   0.8491   0.1195
  -2.000   0.2512   0.01108   0.00383  -0.1057   0.8425   0.2553
  -1.750   0.2765   0.01030   0.00376  -0.1056   0.8366   0.4839
  -1.500   0.3020   0.01010   0.00380  -0.1050   0.8301   0.5849
  -1.250   0.3275   0.01002   0.00385  -0.1041   0.8231   0.6539
  -1.000   0.3526   0.00998   0.00389  -0.1032   0.8157   0.7023
  -0.750   0.3779   0.00995   0.00387  -0.1022   0.8079   0.7381
  -0.500   0.4035   0.00991   0.00380  -0.1015   0.7982   0.7564
  -0.250   0.4307   0.00986   0.00368  -0.1011   0.7884   0.7663
   0.000   0.4581   0.00982   0.00355  -0.1008   0.7787   0.7770
   0.250   0.4843   0.00978   0.00349  -0.1003   0.7679   0.7874
   0.500   0.5108   0.00976   0.00343  -0.0999   0.7573   0.7985
   0.750   0.5372   0.00973   0.00337  -0.0994   0.7465   0.8107
   1.000   0.5633   0.00970   0.00331  -0.0988   0.7349   0.8241
   1.250   0.5893   0.00968   0.00327  -0.0982   0.7234   0.8393
   1.500   0.6152   0.00966   0.00327  -0.0977   0.7123   0.8575
   1.750   0.6412   0.00961   0.00326  -0.0971   0.7006   0.8823
   2.000   0.6732   0.00954   0.00325  -0.0978   0.6882   0.9327
   2.250   0.7039   0.00961   0.00326  -0.0985   0.6748   1.0000
   2.500   0.7310   0.00973   0.00332  -0.0984   0.6600   1.0000
   2.750   0.7578   0.00987   0.00339  -0.0982   0.6437   1.0000
   3.000   0.7842   0.01002   0.00350  -0.0979   0.6263   1.0000
   3.250   0.8101   0.01019   0.00361  -0.0976   0.6057   1.0000
   3.500   0.8353   0.01040   0.00372  -0.0970   0.5815   1.0000
   3.750   0.8599   0.01064   0.00387  -0.0964   0.5538   1.0000
   4.000   0.8835   0.01095   0.00407  -0.0957   0.5212   1.0000
   4.250   0.9059   0.01134   0.00429  -0.0947   0.4850   1.0000
   4.500   0.9276   0.01178   0.00456  -0.0937   0.4476   1.0000
   4.750   0.9488   0.01228   0.00489  -0.0926   0.4113   1.0000
   5.000   0.9699   0.01279   0.00525  -0.0916   0.3774   1.0000
   5.250   0.9913   0.01330   0.00567  -0.0906   0.3477   1.0000
   5.500   1.0128   0.01379   0.00607  -0.0897   0.3225   1.0000
   5.750   1.0342   0.01430   0.00650  -0.0887   0.3024   1.0000
   6.000   1.0561   0.01478   0.00694  -0.0879   0.2857   1.0000
   6.250   1.0778   0.01526   0.00740  -0.0870   0.2714   1.0000
   6.500   1.0994   0.01574   0.00791  -0.0861   0.2579   1.0000
   6.750   1.1209   0.01623   0.00841  -0.0853   0.2459   1.0000
   7.000   1.1421   0.01671   0.00890  -0.0843   0.2291   1.0000
   7.250   1.1614   0.01729   0.00939  -0.0832   0.2034   1.0000
   7.500   1.1807   0.01787   0.00990  -0.0821   0.1780   1.0000
   7.750   1.2006   0.01841   0.01045  -0.0810   0.1585   1.0000
   8.000   1.2180   0.01914   0.01112  -0.0796   0.1328   1.0000
   8.250   1.2326   0.02009   0.01190  -0.0779   0.1026   1.0000
   8.500   1.2417   0.02143   0.01294  -0.0755   0.0630   1.0000
   8.750   1.2502   0.02274   0.01406  -0.0729   0.0336   1.0000
   9.000   1.2562   0.02425   0.01542  -0.0700   0.0143   1.0000
   9.250   1.2663   0.02543   0.01665  -0.0677   0.0096   1.0000
   9.500   1.2765   0.02662   0.01794  -0.0654   0.0081   1.0000
   9.750   1.2876   0.02772   0.01921  -0.0634   0.0075   1.0000
  10.000   1.2972   0.02895   0.02060  -0.0613   0.0069   1.0000
  10.250   1.3056   0.03029   0.02214  -0.0593   0.0065   1.0000
  10.500   1.3126   0.03176   0.02377  -0.0572   0.0062   1.0000
  10.750   1.3180   0.03339   0.02556  -0.0552   0.0060   1.0000
  11.000   1.3214   0.03524   0.02757  -0.0532   0.0058   1.0000
  11.250   1.3229   0.03730   0.02979  -0.0513   0.0056   1.0000
  11.500   1.3226   0.03962   0.03228  -0.0495   0.0055   1.0000
  11.750   1.3208   0.04218   0.03499  -0.0480   0.0054   1.0000
  12.000   1.3169   0.04509   0.03806  -0.0466   0.0053   1.0000
  12.250   1.3122   0.04823   0.04137  -0.0455   0.0052   1.0000
  12.500   1.3082   0.05147   0.04476  -0.0448   0.0052   1.0000
  12.750   1.3052   0.05476   0.04821  -0.0443   0.0052   1.0000
  13.000   1.3010   0.05832   0.05195  -0.0441   0.0051   1.0000
  13.250   1.2967   0.06207   0.05586  -0.0442   0.0051   1.0000
  13.500   1.2922   0.06600   0.05997  -0.0445   0.0051   1.0000
  13.750   1.2872   0.07015   0.06430  -0.0452   0.0050   1.0000
  14.000   1.2815   0.07462   0.06895  -0.0462   0.0050   1.0000
  14.250   1.2750   0.07940   0.07392  -0.0475   0.0049   1.0000
  14.500   1.2683   0.08444   0.07915  -0.0493   0.0048   1.0000
  14.750   1.2604   0.08989   0.08480  -0.0515   0.0047   1.0000
  15.000   1.2513   0.09578   0.09088  -0.0540   0.0047   1.0000
  15.250   1.2418   0.10196   0.09724  -0.0570   0.0047   1.0000
  15.500   1.2323   0.10840   0.10392  -0.0604   0.0045   1.0000
  15.750   1.2219   0.11525   0.11094  -0.0640   0.0045   1.0000
  16.000   1.2110   0.12240   0.11826  -0.0680   0.0045   1.0000
  16.250   1.2002   0.12977   0.12581  -0.0723   0.0045   1.0000
  16.500   1.1891   0.13745   0.13365  -0.0769   0.0045   1.0000
  16.750   1.1776   0.14546   0.14182  -0.0818   0.0045   1.0000
  17.000   1.1663   0.15370   0.15020  -0.0869   0.0045   1.0000
  17.250   1.1545   0.16237   0.15897  -0.0923   0.0046   1.0000
  17.500   1.1424   0.17146   0.16819  -0.0980   0.0047   1.0000
  17.750   1.1302   0.18111   0.17795  -0.1040   0.0048   1.0000
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