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

EPPLER 407 AIRFOIL (e407-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 407 AIRFOIL (e407-il)
Reynolds number: 100,000
Max Cl/Cd: 48.23 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e407-il-100000-n5.txt
Download as CSV file: xf-e407-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 407 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  -0.5092   0.09804   0.09335  -0.0519   0.9974   0.0177
 -10.500  -0.5250   0.08830   0.08358  -0.0589   0.9950   0.0173
 -10.250  -0.5460   0.07957   0.07473  -0.0657   0.9919   0.0170
 -10.000  -0.5646   0.07311   0.06813  -0.0705   0.9880   0.0167
  -9.750  -0.5848   0.06732   0.06214  -0.0745   0.9842   0.0167
  -9.500  -0.6032   0.06319   0.05783  -0.0758   0.9792   0.0164
  -9.250  -0.6208   0.05991   0.05437  -0.0759   0.9738   0.0163
  -9.000  -0.6313   0.05610   0.05027  -0.0773   0.9689   0.0163
  -8.750  -0.6380   0.05257   0.04641  -0.0770   0.9632   0.0165
  -8.500  -0.6329   0.04890   0.04233  -0.0778   0.9595   0.0166
  -8.250  -0.6209   0.04526   0.03821  -0.0788   0.9566   0.0169
  -8.000  -0.6133   0.04256   0.03515  -0.0775   0.9522   0.0172
  -7.750  -0.5968   0.03997   0.03212  -0.0773   0.9493   0.0177
  -7.500  -0.5748   0.03770   0.02945  -0.0774   0.9470   0.0183
  -7.250  -0.5498   0.03584   0.02731  -0.0777   0.9451   0.0190
  -7.000  -0.5299   0.03429   0.02574  -0.0778   0.9426   0.0208
  -6.750  -0.5126   0.03327   0.02462  -0.0769   0.9391   0.0232
  -6.500  -0.4896   0.03212   0.02328  -0.0765   0.9362   0.0257
  -6.250  -0.4656   0.03060   0.02171  -0.0768   0.9339   0.0283
  -6.000  -0.4376   0.02959   0.02063  -0.0779   0.9320   0.0335
  -5.750  -0.4113   0.02852   0.01949  -0.0789   0.9298   0.0410
  -5.500  -0.3910   0.02758   0.01855  -0.0785   0.9259   0.0525
  -5.250  -0.3638   0.02669   0.01769  -0.0796   0.9231   0.0733
  -5.000  -0.3327   0.02556   0.01686  -0.0818   0.9210   0.1190
  -4.750  -0.2973   0.02424   0.01606  -0.0854   0.9195   0.2221
  -4.500  -0.2617   0.02299   0.01595  -0.0888   0.9183   0.4294
  -4.250  -0.2407   0.02343   0.01659  -0.0870   0.9145   0.5165
  -4.000  -0.2172   0.02390   0.01695  -0.0860   0.9103   0.5543
  -3.750  -0.1887   0.02439   0.01728  -0.0859   0.9072   0.5794
  -3.500  -0.1588   0.02491   0.01765  -0.0858   0.9048   0.5979
  -3.250  -0.1367   0.02533   0.01794  -0.0845   0.9007   0.6110
  -3.000  -0.1146   0.02568   0.01818  -0.0833   0.8961   0.6227
  -2.750  -0.0853   0.02596   0.01831  -0.0835   0.8930   0.6343
  -2.500  -0.0552   0.02627   0.01851  -0.0837   0.8906   0.6444
  -2.250  -0.0376   0.02655   0.01872  -0.0816   0.8851   0.6518
  -2.000  -0.0082   0.02664   0.01867  -0.0825   0.8812   0.6616
  -1.750   0.0200   0.02676   0.01873  -0.0823   0.8781   0.6657
  -1.500   0.0548   0.02673   0.01859  -0.0839   0.8760   0.6703
  -1.250   0.0776   0.02673   0.01847  -0.0841   0.8694   0.6760
  -1.000   0.1062   0.02673   0.01843  -0.0843   0.8656   0.6787
  -0.750   0.1399   0.02668   0.01832  -0.0857   0.8630   0.6820
  -0.500   0.1633   0.02674   0.01832  -0.0855   0.8570   0.6861
  -0.250   0.1963   0.02668   0.01817  -0.0873   0.8527   0.6907
   0.000   0.2289   0.02660   0.01808  -0.0882   0.8497   0.6932
   0.250   0.2518   0.02668   0.01815  -0.0877   0.8434   0.6962
   0.500   0.2822   0.02663   0.01808  -0.0886   0.8384   0.6997
   0.750   0.3209   0.02645   0.01786  -0.0911   0.8356   0.7039
   1.000   0.3424   0.02654   0.01797  -0.0904   0.8278   0.7067
   1.250   0.3740   0.02640   0.01786  -0.0912   0.8234   0.7093
   1.500   0.4113   0.02615   0.01762  -0.0930   0.8206   0.7125
   1.750   0.4322   0.02629   0.01779  -0.0923   0.8112   0.7163
   2.000   0.4706   0.02598   0.01750  -0.0945   0.8078   0.7197
   2.250   0.4910   0.02607   0.01765  -0.0933   0.7987   0.7222
   2.500   0.5256   0.02573   0.01738  -0.0944   0.7944   0.7252
   2.750   0.5501   0.02573   0.01746  -0.0941   0.7855   0.7286
   3.000   0.5874   0.02531   0.01709  -0.0958   0.7806   0.7323
   3.250   0.6121   0.02523   0.01710  -0.0954   0.7711   0.7351
   3.500   0.6466   0.02469   0.01668  -0.0961   0.7660   0.7379
   3.750   0.6702   0.02461   0.01669  -0.0954   0.7554   0.7413
   4.000   0.7096   0.02391   0.01609  -0.0971   0.7504   0.7449
   4.250   0.7351   0.02380   0.01610  -0.0968   0.7381   0.7484
   4.750   0.7871   0.02328   0.01584  -0.0956   0.7126   0.7544
   5.000   0.8173   0.02293   0.01562  -0.0957   0.6981   0.7582
   5.500   0.8840   0.02202   0.01492  -0.0968   0.6630   0.7650
   5.750   0.9174   0.02159   0.01455  -0.0972   0.6382   0.7682
   6.000   0.9548   0.02115   0.01415  -0.0983   0.6062   0.7720
   6.250   0.9915   0.02097   0.01388  -0.0994   0.5653   0.7762
   6.500   1.0186   0.02112   0.01391  -0.0990   0.5212   0.7794
   6.750   1.0392   0.02158   0.01421  -0.0977   0.4751   0.7829
   7.000   1.0563   0.02225   0.01471  -0.0960   0.4299   0.7870
   7.250   1.0713   0.02305   0.01538  -0.0942   0.3864   0.7914
   7.500   1.0824   0.02391   0.01609  -0.0917   0.3460   0.7952
   7.750   1.0937   0.02486   0.01690  -0.0895   0.3058   0.7996
   8.000   1.1060   0.02590   0.01780  -0.0876   0.2675   0.8044
   8.250   1.1157   0.02698   0.01875  -0.0853   0.2319   0.8084
   8.500   1.1263   0.02810   0.01977  -0.0832   0.1984   0.8129
   8.750   1.1376   0.02932   0.02087  -0.0814   0.1673   0.8182
   9.000   1.1478   0.03052   0.02201  -0.0794   0.1413   0.8230
   9.250   1.1575   0.03183   0.02329  -0.0775   0.1191   0.8283
   9.500   1.1689   0.03317   0.02462  -0.0759   0.0995   0.8340
   9.750   1.1773   0.03455   0.02601  -0.0738   0.0839   0.8393
  10.000   1.1864   0.03605   0.02753  -0.0720   0.0716   0.8456
  10.250   1.1940   0.03757   0.02913  -0.0699   0.0620   0.8520
  10.500   1.1992   0.03936   0.03092  -0.0679   0.0551   0.8593
  10.750   1.2067   0.04091   0.03268  -0.0659   0.0491   0.8671
  11.000   1.2104   0.04288   0.03469  -0.0639   0.0444   0.8760
  11.250   1.2164   0.04452   0.03655  -0.0618   0.0401   0.8866
  11.500   1.2203   0.04631   0.03850  -0.0597   0.0370   0.9007
  11.750   1.2202   0.04825   0.04060  -0.0573   0.0347   0.9250
  12.000   1.2218   0.05036   0.04287  -0.0555   0.0324   1.0000
  12.250   1.2312   0.05267   0.04539  -0.0550   0.0294   1.0000
  12.500   1.2378   0.05520   0.04805  -0.0545   0.0272   1.0000
  12.750   1.2421   0.05803   0.05098  -0.0539   0.0256   1.0000
  13.000   1.2461   0.06117   0.05423  -0.0533   0.0241   1.0000
  13.250   1.2511   0.06414   0.05750  -0.0529   0.0224   1.0000
  13.500   1.2531   0.06735   0.06095  -0.0527   0.0209   1.0000
  13.750   1.2532   0.07081   0.06459  -0.0526   0.0198   1.0000
  14.000   1.2520   0.07454   0.06850  -0.0527   0.0190   1.0000
  14.250   1.2492   0.07854   0.07265  -0.0531   0.0184   1.0000
  14.500   1.2442   0.08296   0.07722  -0.0537   0.0177   1.0000
  14.750   1.2361   0.08807   0.08255  -0.0547   0.0172   1.0000
  15.000   1.2260   0.09359   0.08839  -0.0564   0.0168   1.0000
  15.250   1.2139   0.09965   0.09475  -0.0587   0.0164   1.0000
  15.500   1.2001   0.10629   0.10167  -0.0618   0.0161   1.0000
  15.750   1.1847   0.11355   0.10920  -0.0657   0.0159   1.0000
  16.000   1.1682   0.12152   0.11741  -0.0704   0.0159   1.0000
  16.250   1.1502   0.13032   0.12644  -0.0761   0.0160   1.0000
  16.500   1.1310   0.14003   0.13635  -0.0826   0.0162   1.0000
  16.750   1.1106   0.15076   0.14725  -0.0901   0.0165   1.0000
  17.000   1.0908   0.16211   0.15871  -0.0979   0.0169   1.0000
  17.250   1.0715   0.17422   0.17088  -0.1059   0.0172   1.0000
<< Back to EPPLER 407 AIRFOIL (e407-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 407 AIRFOIL (e407-il)