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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 200,000
Max Cl/Cd: 78.42 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e176-il-200000-n5.txt
Download as CSV file: xf-e176-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E176  (8.83%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3968   0.08592   0.08265  -0.0262   1.0000   0.0269
  -8.000  -0.3925   0.08291   0.07969  -0.0272   1.0000   0.0275
  -7.750  -0.3928   0.07932   0.07616  -0.0292   1.0000   0.0274
  -7.500  -0.3953   0.07499   0.07190  -0.0329   1.0000   0.0270
  -7.250  -0.3856   0.07337   0.07031  -0.0332   1.0000   0.0302
  -7.000  -0.3676   0.06253   0.05936  -0.0492   0.9652   0.0250
  -6.750  -0.3495   0.05814   0.05490  -0.0534   0.9372   0.0231
  -6.250  -0.3150   0.03963   0.03550  -0.0661   0.8850   0.0174
  -6.000  -0.2997   0.03504   0.03052  -0.0672   0.8659   0.0171
  -5.750  -0.2819   0.03100   0.02602  -0.0677   0.8495   0.0168
  -5.500  -0.2620   0.02748   0.02197  -0.0676   0.8350   0.0166
  -5.250  -0.2401   0.02459   0.01852  -0.0673   0.8220   0.0165
  -5.000  -0.2166   0.02222   0.01564  -0.0669   0.8101   0.0165
  -4.750  -0.1919   0.02036   0.01333  -0.0664   0.7991   0.0167
  -4.500  -0.1664   0.01887   0.01147  -0.0659   0.7885   0.0170
  -4.250  -0.1404   0.01767   0.00998  -0.0654   0.7783   0.0173
  -4.000  -0.1143   0.01666   0.00873  -0.0650   0.7690   0.0179
  -3.750  -0.0889   0.01555   0.00749  -0.0647   0.7601   0.0197
  -3.500  -0.0625   0.01483   0.00664  -0.0643   0.7514   0.0206
  -3.250  -0.0362   0.01417   0.00583  -0.0639   0.7435   0.0212
  -3.000  -0.0094   0.01361   0.00516  -0.0637   0.7352   0.0219
  -2.750   0.0175   0.01317   0.00458  -0.0634   0.7280   0.0229
  -2.500   0.0447   0.01281   0.00407  -0.0631   0.7204   0.0245
  -2.250   0.0719   0.01247   0.00363  -0.0629   0.7136   0.0280
  -2.000   0.0992   0.01211   0.00329  -0.0627   0.7065   0.0445
  -1.750   0.1255   0.01157   0.00306  -0.0627   0.7002   0.1276
  -1.500   0.1518   0.01106   0.00292  -0.0627   0.6933   0.2370
  -1.250   0.1780   0.01070   0.00280  -0.0625   0.6876   0.3343
  -1.000   0.2009   0.00990   0.00282  -0.0618   0.6809   0.5592
  -0.750   0.2196   0.00919   0.00284  -0.0593   0.6754   0.7863
  -0.500   0.2685   0.00889   0.00269  -0.0629   0.6692   0.9793
  -0.250   0.3005   0.00894   0.00260  -0.0638   0.6631   1.0000
   0.000   0.3271   0.00902   0.00255  -0.0635   0.6576   1.0000
   0.250   0.3540   0.00910   0.00253  -0.0633   0.6514   1.0000
   0.500   0.3808   0.00920   0.00251  -0.0631   0.6462   1.0000
   0.750   0.4079   0.00928   0.00253  -0.0629   0.6401   1.0000
   1.000   0.4349   0.00938   0.00255  -0.0627   0.6345   1.0000
   1.250   0.4620   0.00949   0.00259  -0.0626   0.6291   1.0000
   1.500   0.4892   0.00959   0.00266  -0.0624   0.6230   1.0000
   1.750   0.5162   0.00970   0.00270  -0.0622   0.6179   1.0000
   2.000   0.5435   0.00981   0.00282  -0.0621   0.6115   1.0000
   2.250   0.5706   0.00992   0.00290  -0.0620   0.6057   1.0000
   2.500   0.5977   0.01004   0.00301  -0.0618   0.5995   1.0000
   2.750   0.6247   0.01015   0.00312  -0.0617   0.5925   1.0000
   3.000   0.6517   0.01027   0.00325  -0.0615   0.5849   1.0000
   3.250   0.6786   0.01038   0.00336  -0.0613   0.5769   1.0000
   3.500   0.7055   0.01049   0.00350  -0.0611   0.5675   1.0000
   3.750   0.7322   0.01061   0.00363  -0.0608   0.5579   1.0000
   4.000   0.7588   0.01073   0.00378  -0.0606   0.5479   1.0000
   4.250   0.7854   0.01085   0.00396  -0.0603   0.5368   1.0000
   4.500   0.8119   0.01098   0.00413  -0.0601   0.5248   1.0000
   4.750   0.8382   0.01112   0.00431  -0.0597   0.5113   1.0000
   5.000   0.8642   0.01128   0.00453  -0.0594   0.4959   1.0000
   5.250   0.8900   0.01146   0.00473  -0.0590   0.4785   1.0000
   5.500   0.9152   0.01167   0.00496  -0.0585   0.4542   1.0000
   5.750   0.9379   0.01205   0.00517  -0.0577   0.4017   1.0000
   6.000   0.9568   0.01287   0.00557  -0.0565   0.3183   1.0000
   6.250   0.9740   0.01400   0.00630  -0.0554   0.2376   1.0000
   6.500   0.9894   0.01538   0.00718  -0.0542   0.1547   1.0000
   6.750   1.0071   0.01648   0.00799  -0.0531   0.1025   1.0000
   7.000   1.0240   0.01764   0.00888  -0.0520   0.0583   1.0000
   7.500   1.0584   0.01980   0.01085  -0.0495   0.0167   1.0000
   7.750   1.0764   0.02074   0.01188  -0.0483   0.0140   1.0000
   8.000   1.0937   0.02169   0.01293  -0.0470   0.0123   1.0000
   8.250   1.1109   0.02258   0.01395  -0.0458   0.0111   1.0000
   8.500   1.1263   0.02360   0.01509  -0.0443   0.0103   1.0000
   8.750   1.1395   0.02473   0.01636  -0.0426   0.0098   1.0000
   9.000   1.1498   0.02601   0.01776  -0.0407   0.0094   1.0000
   9.250   1.1566   0.02731   0.01918  -0.0383   0.0092   1.0000
   9.500   1.1605   0.02889   0.02087  -0.0357   0.0089   1.0000
   9.750   1.1635   0.03070   0.02279  -0.0335   0.0087   1.0000
  10.000   1.1672   0.03268   0.02486  -0.0316   0.0086   1.0000
  10.250   1.1746   0.03444   0.02680  -0.0301   0.0085   1.0000
  10.500   1.1824   0.03632   0.02882  -0.0287   0.0084   1.0000
  10.750   1.1904   0.03830   0.03093  -0.0274   0.0084   1.0000
  11.000   1.1984   0.04038   0.03318  -0.0263   0.0083   1.0000
  11.250   1.2055   0.04270   0.03569  -0.0251   0.0082   1.0000
  11.500   1.2113   0.04514   0.03832  -0.0241   0.0082   1.0000
  11.750   1.2151   0.04784   0.04125  -0.0233   0.0081   1.0000
  12.000   1.2167   0.05076   0.04439  -0.0226   0.0081   1.0000
  12.250   1.2155   0.05395   0.04783  -0.0222   0.0080   1.0000
  12.500   1.2120   0.05743   0.05155  -0.0221   0.0079   1.0000
  12.750   1.2062   0.06129   0.05566  -0.0223   0.0078   1.0000
  13.000   1.1984   0.06544   0.06005  -0.0230   0.0077   1.0000
  13.250   1.1892   0.06991   0.06475  -0.0242   0.0075   1.0000
  13.500   1.1775   0.07506   0.07013  -0.0258   0.0076   1.0000
  13.750   1.1640   0.08065   0.07594  -0.0281   0.0074   1.0000
  14.000   1.1493   0.08683   0.08233  -0.0309   0.0075   1.0000
  14.250   1.1335   0.09363   0.08934  -0.0343   0.0075   1.0000
  14.500   1.1172   0.10107   0.09698  -0.0385   0.0075   1.0000
  14.750   1.0995   0.10944   0.10554  -0.0435   0.0075   1.0000
  15.000   1.0814   0.11855   0.11482  -0.0491   0.0076   1.0000
  15.250   1.0622   0.12883   0.12526  -0.0556   0.0078   1.0000
  15.500   1.0433   0.13979   0.13634  -0.0624   0.0081   1.0000
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