Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E64 (8.45%) (e64-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 50,000
Max Cl/Cd: 42.52 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e64-il-50000-n5.txt
Download as CSV file: xf-e64-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E64  (8.45%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3901   0.09545   0.08856  -0.0346   1.0000   0.0524
  -7.750  -0.3961   0.09240   0.08562  -0.0344   1.0000   0.0500
  -7.250  -0.4171   0.08493   0.07840  -0.0381   1.0000   0.0446
  -7.000  -0.4173   0.08179   0.07533  -0.0378   1.0000   0.0438
  -6.750  -0.4180   0.07834   0.07193  -0.0385   1.0000   0.0430
  -6.500  -0.4178   0.07457   0.06821  -0.0399   1.0000   0.0423
  -6.250  -0.4158   0.07048   0.06413  -0.0418   1.0000   0.0414
  -6.000  -0.4117   0.06600   0.05962  -0.0442   1.0000   0.0405
  -5.750  -0.4045   0.06115   0.05466  -0.0470   1.0000   0.0396
  -5.500  -0.3933   0.05602   0.04933  -0.0502   1.0000   0.0388
  -5.250  -0.3775   0.05095   0.04395  -0.0534   1.0000   0.0382
  -5.000  -0.3579   0.04639   0.03901  -0.0562   1.0000   0.0386
  -4.750  -0.3350   0.04239   0.03454  -0.0586   1.0000   0.0397
  -4.500  -0.3095   0.03867   0.03027  -0.0605   1.0000   0.0409
  -4.250  -0.2823   0.03544   0.02641  -0.0620   1.0000   0.0420
  -4.000  -0.2545   0.03264   0.02303  -0.0628   1.0000   0.0427
  -3.750  -0.2268   0.03034   0.02019  -0.0632   1.0000   0.0437
  -3.500  -0.1998   0.02854   0.01792  -0.0630   1.0000   0.0452
  -3.250  -0.1747   0.02693   0.01619  -0.0628   1.0000   0.0479
  -3.000  -0.1506   0.02591   0.01499  -0.0624   1.0000   0.0543
  -2.750  -0.1262   0.02490   0.01381  -0.0620   1.0000   0.0622
  -2.500  -0.1000   0.02391   0.01269  -0.0619   1.0000   0.0766
  -2.250  -0.0711   0.02273   0.01179  -0.0628   1.0000   0.1378
  -2.000  -0.0413   0.02137   0.01136  -0.0643   1.0000   0.3180
  -1.750  -0.0137   0.02070   0.01135  -0.0646   0.9976   0.4996
  -1.500   0.0127   0.02029   0.01145  -0.0637   0.9910   0.6688
  -1.250   0.0346   0.01985   0.01136  -0.0612   0.9828   0.8777
  -1.000   0.0763   0.01997   0.01105  -0.0646   0.9734   1.0000
  -0.750   0.1125   0.02027   0.01093  -0.0669   0.9649   1.0000
  -0.500   0.1505   0.02062   0.01093  -0.0695   0.9572   1.0000
  -0.250   0.1875   0.02094   0.01096  -0.0718   0.9488   1.0000
   0.000   0.2219   0.02123   0.01100  -0.0736   0.9395   1.0000
   0.250   0.2604   0.02155   0.01111  -0.0760   0.9314   1.0000
   0.500   0.2945   0.02181   0.01122  -0.0776   0.9214   1.0000
   0.750   0.3278   0.02207   0.01135  -0.0790   0.9112   1.0000
   1.000   0.3646   0.02231   0.01148  -0.0810   0.9021   1.0000
   1.250   0.4000   0.02252   0.01163  -0.0826   0.8921   1.0000
   1.500   0.4318   0.02274   0.01180  -0.0835   0.8806   1.0000
   1.750   0.4652   0.02291   0.01196  -0.0847   0.8695   1.0000
   2.000   0.5017   0.02301   0.01207  -0.0862   0.8592   1.0000
   2.250   0.5383   0.02306   0.01216  -0.0877   0.8485   1.0000
   2.500   0.5704   0.02314   0.01229  -0.0883   0.8358   1.0000
   2.750   0.6032   0.02319   0.01241  -0.0890   0.8228   1.0000
   3.000   0.6363   0.02320   0.01251  -0.0896   0.8095   1.0000
   3.250   0.6693   0.02316   0.01260  -0.0900   0.7955   1.0000
   3.500   0.7023   0.02307   0.01263  -0.0903   0.7806   1.0000
   3.750   0.7356   0.02292   0.01262  -0.0906   0.7648   1.0000
   4.000   0.7695   0.02273   0.01261  -0.0907   0.7481   1.0000
   4.250   0.7974   0.02271   0.01273  -0.0900   0.7275   1.0000
   4.500   0.8293   0.02253   0.01270  -0.0897   0.7064   1.0000
   4.750   0.8575   0.02248   0.01284  -0.0889   0.6817   1.0000
   5.000   0.8863   0.02243   0.01292  -0.0881   0.6546   1.0000
   5.250   0.9138   0.02245   0.01305  -0.0871   0.6239   1.0000
   5.500   0.9409   0.02253   0.01319  -0.0859   0.5897   1.0000
   5.750   0.9641   0.02280   0.01356  -0.0843   0.5507   1.0000
   6.000   0.9860   0.02319   0.01394  -0.0826   0.5082   1.0000
   6.250   1.0058   0.02374   0.01444  -0.0806   0.4624   1.0000
   6.500   1.0234   0.02448   0.01507  -0.0785   0.4148   1.0000
   6.750   1.0389   0.02539   0.01589  -0.0763   0.3659   1.0000
   7.000   1.0527   0.02648   0.01688  -0.0740   0.3178   1.0000
   7.250   1.0649   0.02775   0.01799  -0.0717   0.2704   1.0000
   7.500   1.0763   0.02919   0.01927  -0.0695   0.2256   1.0000
   7.750   1.0865   0.03081   0.02074  -0.0673   0.1834   1.0000
   8.000   1.0944   0.03264   0.02232  -0.0651   0.1396   1.0000
   8.250   1.1011   0.03457   0.02398  -0.0630   0.1003   1.0000
   8.500   1.1084   0.03671   0.02599  -0.0607   0.0767   1.0000
   8.750   1.1169   0.03895   0.02827  -0.0585   0.0634   1.0000
   9.000   1.1256   0.04124   0.03059  -0.0564   0.0564   1.0000
   9.250   1.1404   0.04341   0.03305  -0.0547   0.0504   1.0000
   9.500   1.1503   0.04567   0.03531  -0.0531   0.0461   1.0000
   9.750   1.1680   0.04806   0.03809  -0.0518   0.0422   1.0000
  10.000   1.1835   0.05070   0.04102  -0.0505   0.0396   1.0000
  10.250   1.1967   0.05354   0.04413  -0.0493   0.0380   1.0000
  10.500   1.2066   0.05659   0.04743  -0.0479   0.0369   1.0000
  10.750   1.2136   0.06000   0.05107  -0.0465   0.0360   1.0000
  11.000   1.2154   0.06382   0.05521  -0.0450   0.0355   1.0000
  11.250   1.2094   0.06765   0.05944  -0.0432   0.0352   1.0000
  11.500   1.1994   0.07176   0.06391  -0.0418   0.0351   1.0000
  11.750   1.1860   0.07621   0.06868  -0.0411   0.0350   1.0000
  12.000   1.1702   0.08109   0.07385  -0.0412   0.0350   1.0000
  12.250   1.1525   0.08649   0.07952  -0.0422   0.0350   1.0000
  12.500   1.1338   0.09248   0.08574  -0.0443   0.0351   1.0000
  12.750   1.1143   0.09914   0.09259  -0.0475   0.0352   1.0000
  13.000   1.0951   0.10646   0.10006  -0.0516   0.0354   1.0000
  13.250   1.0738   0.11500   0.10875  -0.0571   0.0357   1.0000
  13.500   1.0278   0.13282   0.12677  -0.0704   0.0375   1.0000
<< Back to E64 (8.45%) (e64-il)

Polar data table (+)

Polar graphs


<< Back to E64 (8.45%) (e64-il)