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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 200,000
Max Cl/Cd: 73.5 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e178-il-200000-n5.txt
Download as CSV file: xf-e178-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E178  (8.69%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3823   0.09182   0.08875  -0.0104   1.0000   0.0148
  -9.000  -0.3905   0.08461   0.08159  -0.0136   1.0000   0.0136
  -8.500  -0.4584   0.08539   0.08215  -0.0152   1.0000   0.0126
  -8.250  -0.4591   0.08106   0.07788  -0.0176   1.0000   0.0125
  -8.000  -0.4615   0.07661   0.07350  -0.0204   1.0000   0.0124
  -7.750  -0.4643   0.07205   0.06900  -0.0240   1.0000   0.0123
  -7.500  -0.4625   0.06616   0.06313  -0.0299   1.0000   0.0123
  -7.250  -0.4580   0.05944   0.05637  -0.0359   1.0000   0.0123
  -7.000  -0.4490   0.05187   0.04865  -0.0418   0.9787   0.0123
  -6.750  -0.4307   0.04211   0.03844  -0.0488   0.9358   0.0124
  -6.500  -0.4188   0.03480   0.03047  -0.0513   0.9070   0.0134
  -6.250  -0.4011   0.03265   0.02805  -0.0515   0.8853   0.0144
  -6.000  -0.3814   0.03097   0.02612  -0.0512   0.8666   0.0158
  -5.750  -0.3632   0.02710   0.02164  -0.0505   0.8508   0.0162
  -5.500  -0.3422   0.02416   0.01812  -0.0497   0.8369   0.0170
  -5.250  -0.3192   0.02191   0.01535  -0.0488   0.8241   0.0179
  -5.000  -0.2944   0.02071   0.01376  -0.0482   0.8124   0.0196
  -4.750  -0.2694   0.01938   0.01206  -0.0475   0.8015   0.0207
  -4.500  -0.2450   0.01750   0.00986  -0.0468   0.7915   0.0214
  -4.250  -0.2196   0.01627   0.00841  -0.0463   0.7815   0.0225
  -4.000  -0.1939   0.01542   0.00742  -0.0458   0.7723   0.0237
  -3.750  -0.1681   0.01475   0.00660  -0.0454   0.7637   0.0250
  -3.500  -0.1417   0.01421   0.00595  -0.0450   0.7549   0.0269
  -3.250  -0.1152   0.01381   0.00541  -0.0447   0.7471   0.0295
  -3.000  -0.0886   0.01335   0.00482  -0.0444   0.7392   0.0304
  -2.750  -0.0620   0.01284   0.00418  -0.0440   0.7318   0.0329
  -2.500  -0.0350   0.01249   0.00372  -0.0437   0.7246   0.0384
  -2.250  -0.0081   0.01210   0.00336  -0.0435   0.7176   0.0610
  -2.000   0.0183   0.01168   0.00310  -0.0434   0.7108   0.1178
  -1.750   0.0448   0.01131   0.00293  -0.0433   0.7042   0.1856
  -1.500   0.0705   0.01082   0.00280  -0.0431   0.6977   0.2949
  -1.250   0.0942   0.01013   0.00272  -0.0426   0.6916   0.4706
  -1.000   0.1133   0.00926   0.00273  -0.0406   0.6853   0.7063
  -0.750   0.1527   0.00880   0.00270  -0.0418   0.6799   0.9175
  -0.500   0.2046   0.00876   0.00254  -0.0468   0.6731   0.9930
  -0.250   0.2351   0.00882   0.00244  -0.0474   0.6676   1.0000
   0.000   0.2613   0.00887   0.00242  -0.0471   0.6612   1.0000
   0.250   0.2873   0.00895   0.00238  -0.0467   0.6556   1.0000
   0.500   0.3137   0.00903   0.00238  -0.0464   0.6497   1.0000
   0.750   0.3401   0.00911   0.00239  -0.0461   0.6437   1.0000
   1.000   0.3665   0.00920   0.00240  -0.0457   0.6385   1.0000
   1.250   0.3932   0.00929   0.00245  -0.0455   0.6321   1.0000
   1.500   0.4197   0.00939   0.00249  -0.0452   0.6269   1.0000
   1.750   0.4465   0.00948   0.00257  -0.0450   0.6205   1.0000
   2.000   0.4732   0.00959   0.00264  -0.0448   0.6146   1.0000
   2.250   0.5000   0.00969   0.00275  -0.0446   0.6082   1.0000
   2.500   0.5267   0.00979   0.00283  -0.0443   0.6009   1.0000
   2.750   0.5535   0.00989   0.00294  -0.0441   0.5924   1.0000
   3.000   0.5801   0.00999   0.00301  -0.0438   0.5847   1.0000
   3.250   0.6069   0.01009   0.00318  -0.0435   0.5749   1.0000
   3.500   0.6335   0.01019   0.00330  -0.0433   0.5648   1.0000
   3.750   0.6601   0.01029   0.00342  -0.0430   0.5542   1.0000
   4.000   0.6865   0.01041   0.00355  -0.0427   0.5424   1.0000
   4.250   0.7129   0.01052   0.00369  -0.0424   0.5295   1.0000
   4.500   0.7393   0.01065   0.00390  -0.0421   0.5154   1.0000
   4.750   0.7655   0.01079   0.00408  -0.0417   0.4988   1.0000
   5.000   0.7913   0.01096   0.00427  -0.0414   0.4786   1.0000
   5.250   0.8169   0.01117   0.00448  -0.0409   0.4537   1.0000
   5.500   0.8416   0.01145   0.00471  -0.0404   0.4214   1.0000
   5.750   0.8655   0.01185   0.00501  -0.0399   0.3772   1.0000
   6.000   0.8873   0.01250   0.00549  -0.0391   0.3169   1.0000
   6.250   0.9075   0.01339   0.00610  -0.0384   0.2535   1.0000
   6.500   0.9264   0.01446   0.00684  -0.0375   0.1879   1.0000
   6.750   0.9442   0.01566   0.00767  -0.0367   0.1250   1.0000
   7.000   0.9630   0.01670   0.00847  -0.0358   0.0820   1.0000
   7.250   0.9816   0.01773   0.00931  -0.0349   0.0501   1.0000
   7.500   0.9992   0.01885   0.01029  -0.0339   0.0252   1.0000
   7.750   1.0166   0.01998   0.01141  -0.0327   0.0148   1.0000
   8.000   1.0328   0.02119   0.01270  -0.0313   0.0117   1.0000
   8.250   1.0498   0.02224   0.01397  -0.0300   0.0107   1.0000
   8.500   1.0651   0.02342   0.01531  -0.0285   0.0098   1.0000
   8.750   1.0787   0.02467   0.01672  -0.0270   0.0092   1.0000
   9.000   1.0904   0.02604   0.01824  -0.0252   0.0088   1.0000
   9.250   1.1008   0.02749   0.01981  -0.0233   0.0084   1.0000
   9.500   1.1093   0.02885   0.02128  -0.0213   0.0079   1.0000
   9.750   1.1155   0.03039   0.02293  -0.0192   0.0074   1.0000
  10.000   1.1185   0.03250   0.02517  -0.0171   0.0069   1.0000
  10.250   1.1237   0.03467   0.02749  -0.0154   0.0065   1.0000
  10.500   1.1322   0.03636   0.02936  -0.0141   0.0062   1.0000
  10.750   1.1383   0.03854   0.03175  -0.0128   0.0061   1.0000
  11.000   1.1431   0.04089   0.03436  -0.0116   0.0060   1.0000
  11.250   1.1452   0.04363   0.03735  -0.0105   0.0058   1.0000
  11.500   1.1455   0.04650   0.04045  -0.0097   0.0058   1.0000
  11.750   1.1431   0.04974   0.04395  -0.0092   0.0057   1.0000
  12.000   1.1380   0.05335   0.04780  -0.0091   0.0057   1.0000
  12.250   1.1302   0.05736   0.05207  -0.0094   0.0056   1.0000
  12.500   1.1204   0.06176   0.05672  -0.0102   0.0056   1.0000
  12.750   1.1090   0.06657   0.06175  -0.0116   0.0056   1.0000
  13.000   1.0940   0.07220   0.06762  -0.0137   0.0056   1.0000
  13.250   1.0795   0.07806   0.07369  -0.0164   0.0056   1.0000
  13.500   1.0637   0.08452   0.08034  -0.0197   0.0057   1.0000
  13.750   1.0463   0.09190   0.08790  -0.0239   0.0057   1.0000
  14.000   1.0276   0.10031   0.09649  -0.0289   0.0057   1.0000
  14.250   1.0099   0.10932   0.10566  -0.0346   0.0057   1.0000
  14.500   0.9917   0.11938   0.11586  -0.0408   0.0058   1.0000
  14.750   0.9723   0.13075   0.12733  -0.0477   0.0059   1.0000
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