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

E207 (12.04%) (e207-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E207 (12.04%) (e207-il)
Reynolds number: 200,000
Max Cl/Cd: 72.11 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e207-il-200000-n5.txt
Download as CSV file: xf-e207-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E207  (12.04%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5099   0.08119   0.07765  -0.0386   1.0000   0.0170
 -10.500  -0.5423   0.06841   0.06487  -0.0465   1.0000   0.0167
 -10.250  -0.5721   0.05786   0.05423  -0.0558   1.0000   0.0164
 -10.000  -0.5977   0.05181   0.04803  -0.0605   1.0000   0.0163
  -9.750  -0.6223   0.04827   0.04436  -0.0596   1.0000   0.0162
  -9.500  -0.6426   0.04485   0.04073  -0.0572   1.0000   0.0162
  -9.250  -0.6569   0.04134   0.03693  -0.0545   1.0000   0.0163
  -9.000  -0.6647   0.03811   0.03336  -0.0517   1.0000   0.0164
  -8.750  -0.6666   0.03528   0.03018  -0.0489   1.0000   0.0166
  -8.500  -0.6641   0.03284   0.02738  -0.0462   1.0000   0.0168
  -8.250  -0.6552   0.03072   0.02490  -0.0442   0.9992   0.0171
  -8.000  -0.6285   0.02769   0.02148  -0.0460   0.9924   0.0177
  -7.750  -0.5978   0.02612   0.01981  -0.0479   0.9854   0.0188
  -7.500  -0.5673   0.02469   0.01815  -0.0493   0.9776   0.0198
  -7.250  -0.5353   0.02301   0.01620  -0.0508   0.9702   0.0203
  -7.000  -0.5066   0.02157   0.01456  -0.0514   0.9587   0.0210
  -6.750  -0.4771   0.02030   0.01311  -0.0520   0.9465   0.0217
  -6.500  -0.4463   0.01918   0.01184  -0.0529   0.9333   0.0224
  -6.250  -0.4139   0.01826   0.01074  -0.0540   0.9187   0.0232
  -6.000  -0.3827   0.01711   0.00953  -0.0551   0.9025   0.0249
  -5.750  -0.3505   0.01635   0.00867  -0.0561   0.8846   0.0265
  -5.500  -0.3210   0.01567   0.00786  -0.0565   0.8639   0.0278
  -5.250  -0.2929   0.01510   0.00712  -0.0564   0.8430   0.0294
  -5.000  -0.2665   0.01463   0.00647  -0.0561   0.8228   0.0312
  -4.750  -0.2415   0.01414   0.00588  -0.0555   0.8031   0.0352
  -4.500  -0.2163   0.01375   0.00539  -0.0549   0.7852   0.0428
  -4.250  -0.1918   0.01332   0.00495  -0.0542   0.7686   0.0635
  -4.000  -0.1674   0.01292   0.00458  -0.0536   0.7531   0.0933
  -3.750  -0.1426   0.01259   0.00428  -0.0531   0.7387   0.1256
  -3.500  -0.1182   0.01223   0.00402  -0.0526   0.7254   0.1711
  -3.250  -0.0938   0.01185   0.00378  -0.0521   0.7129   0.2257
  -3.000  -0.0708   0.01135   0.00359  -0.0514   0.7014   0.3157
  -2.750  -0.0470   0.01102   0.00348  -0.0507   0.6908   0.3957
  -2.500  -0.0220   0.01085   0.00338  -0.0501   0.6805   0.4487
  -2.250   0.0032   0.01071   0.00330  -0.0495   0.6706   0.4944
  -2.000   0.0285   0.01059   0.00322  -0.0489   0.6616   0.5355
  -1.750   0.0542   0.01050   0.00315  -0.0483   0.6527   0.5696
  -1.500   0.0800   0.01041   0.00310  -0.0478   0.6443   0.6021
  -1.250   0.1055   0.01033   0.00304  -0.0472   0.6365   0.6349
  -1.000   0.1311   0.01025   0.00302  -0.0465   0.6286   0.6690
  -0.750   0.1566   0.01018   0.00300  -0.0458   0.6215   0.7053
  -0.500   0.1821   0.01010   0.00301  -0.0451   0.6140   0.7437
  -0.250   0.2079   0.01004   0.00302  -0.0443   0.6073   0.7858
   0.000   0.2359   0.01000   0.00307  -0.0440   0.6002   0.8313
   0.250   0.2696   0.01003   0.00312  -0.0448   0.5935   0.8751
   0.500   0.3087   0.01010   0.00317  -0.0469   0.5865   0.9108
   0.750   0.3481   0.01019   0.00320  -0.0492   0.5796   0.9364
   1.000   0.3844   0.01028   0.00325  -0.0509   0.5731   0.9567
   1.250   0.4211   0.01037   0.00328  -0.0528   0.5662   0.9718
   1.500   0.4590   0.01047   0.00331  -0.0550   0.5600   0.9838
   1.750   0.4982   0.01053   0.00335  -0.0575   0.5530   0.9933
   2.000   0.5343   0.01062   0.00337  -0.0594   0.5472   1.0000
   2.250   0.5578   0.01071   0.00347  -0.0587   0.5407   1.0000
   2.500   0.5814   0.01083   0.00355  -0.0579   0.5350   1.0000
   2.750   0.6052   0.01095   0.00366  -0.0571   0.5288   1.0000
   3.000   0.6291   0.01107   0.00377  -0.0564   0.5227   1.0000
   3.250   0.6531   0.01121   0.00390  -0.0557   0.5169   1.0000
   3.500   0.6771   0.01133   0.00405  -0.0550   0.5100   1.0000
   3.750   0.7011   0.01148   0.00417  -0.0542   0.5037   1.0000
   4.000   0.7251   0.01161   0.00433  -0.0535   0.4955   1.0000
   4.250   0.7489   0.01176   0.00449  -0.0527   0.4882   1.0000
   4.500   0.7727   0.01190   0.00466  -0.0519   0.4794   1.0000
   4.750   0.7965   0.01205   0.00483  -0.0511   0.4705   1.0000
   5.000   0.8200   0.01221   0.00499  -0.0503   0.4613   1.0000
   5.250   0.8438   0.01236   0.00521  -0.0495   0.4509   1.0000
   5.500   0.8674   0.01253   0.00541  -0.0487   0.4404   1.0000
   5.750   0.8907   0.01271   0.00562  -0.0479   0.4295   1.0000
   6.000   0.9138   0.01291   0.00584  -0.0470   0.4172   1.0000
   6.250   0.9367   0.01312   0.00609  -0.0461   0.4033   1.0000
   6.500   0.9593   0.01335   0.00635  -0.0452   0.3875   1.0000
   6.750   0.9814   0.01361   0.00664  -0.0442   0.3693   1.0000
   7.000   1.0024   0.01393   0.00694  -0.0431   0.3479   1.0000
   7.250   1.0226   0.01431   0.00729  -0.0419   0.3221   1.0000
   7.500   1.0409   0.01482   0.00772  -0.0404   0.2911   1.0000
   7.750   1.0572   0.01546   0.00823  -0.0387   0.2543   1.0000
   8.000   1.0717   0.01624   0.00885  -0.0367   0.2194   1.0000
   8.250   1.0860   0.01705   0.00954  -0.0349   0.1886   1.0000
   8.500   1.0996   0.01788   0.01028  -0.0329   0.1625   1.0000
   9.000   1.1234   0.01967   0.01191  -0.0287   0.1154   1.0000
   9.250   1.1327   0.02064   0.01279  -0.0262   0.0955   1.0000
   9.500   1.1395   0.02160   0.01366  -0.0234   0.0778   1.0000
   9.750   1.1449   0.02261   0.01461  -0.0205   0.0635   1.0000
  10.000   1.1514   0.02363   0.01560  -0.0180   0.0531   1.0000
  10.250   1.1581   0.02470   0.01669  -0.0157   0.0451   1.0000
  10.500   1.1635   0.02592   0.01793  -0.0135   0.0391   1.0000
  10.750   1.1696   0.02717   0.01924  -0.0116   0.0327   1.0000
  11.000   1.1735   0.02868   0.02080  -0.0098   0.0274   1.0000
  11.250   1.1750   0.03050   0.02267  -0.0082   0.0225   1.0000
  11.500   1.1783   0.03230   0.02456  -0.0070   0.0194   1.0000
  11.750   1.1777   0.03456   0.02683  -0.0058   0.0163   1.0000
  12.000   1.1800   0.03668   0.02909  -0.0050   0.0148   1.0000
  12.250   1.1822   0.03889   0.03141  -0.0045   0.0138   1.0000
  12.500   1.1823   0.04141   0.03400  -0.0041   0.0127   1.0000
  12.750   1.1808   0.04419   0.03687  -0.0038   0.0117   1.0000
  13.000   1.1806   0.04692   0.03975  -0.0037   0.0113   1.0000
  13.250   1.1796   0.04980   0.04275  -0.0037   0.0110   1.0000
  13.500   1.1778   0.05286   0.04594  -0.0039   0.0104   1.0000
  13.750   1.1757   0.05602   0.04923  -0.0043   0.0102   1.0000
  14.000   1.1732   0.05931   0.05264  -0.0048   0.0099   1.0000
  14.250   1.1699   0.06282   0.05628  -0.0054   0.0097   1.0000
  14.500   1.1662   0.06650   0.06009  -0.0063   0.0094   1.0000
  14.750   1.1625   0.07028   0.06399  -0.0072   0.0093   1.0000
  15.000   1.1578   0.07435   0.06818  -0.0084   0.0091   1.0000
  15.250   1.1520   0.07866   0.07259  -0.0098   0.0089   1.0000
  15.500   1.1464   0.08304   0.07708  -0.0112   0.0088   1.0000
  15.750   1.1409   0.08753   0.08168  -0.0127   0.0087   1.0000
<< Back to E207 (12.04%) (e207-il)

Polar data table (+)

Polar graphs


<< Back to E207 (12.04%) (e207-il)