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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 100,000
Max Cl/Cd: 63.5 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq358-il-100000-n5.txt
Download as CSV file: xf-hq358-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/8 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3501   0.09173   0.08718  -0.0317   1.0000   0.0343
  -7.250  -0.3580   0.09002   0.08557  -0.0297   1.0000   0.0360
  -7.000  -0.3700   0.08850   0.08414  -0.0274   1.0000   0.0357
  -6.750  -0.3791   0.08665   0.08238  -0.0260   1.0000   0.0361
  -6.500  -0.3860   0.08447   0.08028  -0.0254   1.0000   0.0369
  -6.250  -0.3807   0.08114   0.07699  -0.0292   0.9978   0.0397
  -6.000  -0.3432   0.07489   0.07061  -0.0461   0.9897   0.0422
  -5.750  -0.3053   0.06969   0.06505  -0.0593   0.9824   0.0430
  -5.500  -0.2906   0.06333   0.05880  -0.0613   0.9781   0.0442
  -5.250  -0.2667   0.05874   0.05418  -0.0647   0.9744   0.0454
  -5.000  -0.2416   0.05433   0.04962  -0.0689   0.9682   0.0461
  -4.750  -0.2029   0.04807   0.04299  -0.0745   0.9638   0.0278
  -4.500  -0.1697   0.04310   0.03774  -0.0793   0.9600   0.0247
  -4.250  -0.1376   0.03858   0.03282  -0.0825   0.9542   0.0225
  -4.000  -0.0978   0.03374   0.02734  -0.0860   0.9506   0.0203
  -3.750  -0.0581   0.03020   0.02318  -0.0887   0.9481   0.0194
  -3.500  -0.0279   0.02771   0.02022  -0.0894   0.9426   0.0191
  -3.250   0.0064   0.02515   0.01719  -0.0910   0.9388   0.0194
  -3.000   0.0418   0.02356   0.01529  -0.0930   0.9359   0.0226
  -2.750   0.0739   0.02206   0.01348  -0.0936   0.9315   0.0254
  -2.500   0.1054   0.02054   0.01170  -0.0940   0.9269   0.0264
  -2.250   0.1402   0.01921   0.01019  -0.0950   0.9236   0.0282
  -2.000   0.1766   0.01813   0.00897  -0.0965   0.9211   0.0308
  -1.750   0.2030   0.01748   0.00821  -0.0963   0.9140   0.0381
  -1.500   0.2377   0.01660   0.00749  -0.0978   0.9102   0.1019
  -1.250   0.2627   0.01462   0.00762  -0.0974   0.9069   0.7081
  -1.000   0.2802   0.01436   0.00752  -0.0943   0.8991   0.8128
  -0.750   0.3179   0.01383   0.00706  -0.0953   0.8955   1.0000
  -0.500   0.3479   0.01390   0.00690  -0.0960   0.8882   1.0000
  -0.250   0.3828   0.01390   0.00664  -0.0974   0.8827   1.0000
   0.000   0.4128   0.01395   0.00652  -0.0979   0.8747   1.0000
   0.250   0.4472   0.01391   0.00633  -0.0991   0.8685   1.0000
   0.500   0.4760   0.01393   0.00625  -0.0992   0.8590   1.0000
   0.750   0.5078   0.01385   0.00606  -0.0997   0.8499   1.0000
   1.000   0.5408   0.01370   0.00581  -0.1002   0.8403   1.0000
   1.250   0.5696   0.01361   0.00566  -0.1000   0.8274   1.0000
   1.500   0.5979   0.01354   0.00553  -0.0997   0.8142   1.0000
   1.750   0.6257   0.01352   0.00550  -0.0994   0.8013   1.0000
   2.000   0.6531   0.01355   0.00551  -0.0992   0.7892   1.0000
   2.250   0.6807   0.01358   0.00553  -0.0989   0.7767   1.0000
   2.500   0.7084   0.01361   0.00556  -0.0986   0.7635   1.0000
   2.750   0.7360   0.01364   0.00565  -0.0983   0.7490   1.0000
   3.000   0.7637   0.01367   0.00569  -0.0980   0.7335   1.0000
   3.250   0.7903   0.01374   0.00579  -0.0975   0.7153   1.0000
   3.500   0.8169   0.01381   0.00589  -0.0970   0.6952   1.0000
   3.750   0.8432   0.01391   0.00600  -0.0964   0.6722   1.0000
   4.000   0.8691   0.01404   0.00621  -0.0957   0.6456   1.0000
   4.250   0.8944   0.01422   0.00637  -0.0949   0.6134   1.0000
   4.500   0.9189   0.01447   0.00657  -0.0939   0.5745   1.0000
   4.750   0.9422   0.01484   0.00680  -0.0928   0.5289   1.0000
   5.000   0.9640   0.01535   0.00714  -0.0915   0.4796   1.0000
   5.250   0.9849   0.01598   0.00759  -0.0902   0.4336   1.0000
   5.500   1.0057   0.01666   0.00823  -0.0890   0.3936   1.0000
   5.750   1.0268   0.01733   0.00885  -0.0879   0.3594   1.0000
   6.000   1.0477   0.01803   0.00951  -0.0868   0.3291   1.0000
   6.250   1.0684   0.01875   0.01022  -0.0857   0.3016   1.0000
   6.500   1.0870   0.01959   0.01095  -0.0844   0.2651   1.0000
   6.750   1.1055   0.02044   0.01173  -0.0831   0.2262   1.0000
   7.000   1.1218   0.02149   0.01249  -0.0817   0.1580   1.0000
   7.250   1.1299   0.02380   0.01396  -0.0796   0.0527   1.0000
   7.500   1.1416   0.02594   0.01589  -0.0773   0.0216   1.0000
   7.750   1.1547   0.02777   0.01788  -0.0751   0.0166   1.0000
   8.000   1.1682   0.02935   0.01971  -0.0730   0.0140   1.0000
   8.250   1.1813   0.03083   0.02141  -0.0710   0.0118   1.0000
   8.500   1.1921   0.03245   0.02325  -0.0689   0.0105   1.0000
   8.750   1.1998   0.03429   0.02531  -0.0663   0.0100   1.0000
   9.000   1.2048   0.03630   0.02751  -0.0635   0.0095   1.0000
   9.250   1.2097   0.03852   0.02993  -0.0608   0.0092   1.0000
   9.500   1.2152   0.04102   0.03263  -0.0583   0.0090   1.0000
   9.750   1.2214   0.04388   0.03572  -0.0562   0.0088   1.0000
  10.000   1.2273   0.04705   0.03916  -0.0541   0.0086   1.0000
  10.250   1.2304   0.05044   0.04286  -0.0521   0.0085   1.0000
  10.500   1.2296   0.05397   0.04671  -0.0500   0.0085   1.0000
  10.750   1.2252   0.05762   0.05068  -0.0481   0.0085   1.0000
  11.000   1.2176   0.06141   0.05477  -0.0465   0.0085   1.0000
  11.250   1.2078   0.06542   0.05907  -0.0454   0.0085   1.0000
  11.500   1.1961   0.06973   0.06366  -0.0450   0.0085   1.0000
  11.750   1.1834   0.07433   0.06851  -0.0452   0.0085   1.0000
  12.000   1.1693   0.07939   0.07382  -0.0463   0.0085   1.0000
  12.250   1.1550   0.08488   0.07954  -0.0483   0.0085   1.0000
  12.500   1.1403   0.09088   0.08576  -0.0511   0.0086   1.0000
  12.750   1.1256   0.09743   0.09251  -0.0547   0.0086   1.0000
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