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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 500,000
Max Cl/Cd: 95.14 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e178-il-500000-n5.txt
Download as CSV file: xf-e178-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4765   0.08488   0.08281  -0.0125   1.0000   0.0059
  -8.500  -0.4789   0.08031   0.07828  -0.0151   1.0000   0.0059
  -8.250  -0.4843   0.07548   0.07350  -0.0179   1.0000   0.0060
  -8.000  -0.4816   0.06813   0.06610  -0.0273   0.9067   0.0061
  -7.750  -0.4870   0.06201   0.05981  -0.0325   0.8632   0.0061
  -7.500  -0.4914   0.05345   0.05105  -0.0387   0.8371   0.0061
  -7.250  -0.5182   0.03112   0.02778  -0.0454   0.8208   0.0061
  -7.000  -0.5105   0.02353   0.01921  -0.0451   0.8069   0.0066
  -6.750  -0.4894   0.02119   0.01641  -0.0446   0.7940   0.0069
  -6.500  -0.4688   0.01856   0.01330  -0.0441   0.7823   0.0076
  -6.250  -0.4438   0.01782   0.01239  -0.0439   0.7710   0.0080
  -6.000  -0.4180   0.01734   0.01174  -0.0437   0.7604   0.0086
  -5.750  -0.3921   0.01672   0.01095  -0.0435   0.7505   0.0095
  -5.500  -0.3659   0.01612   0.01017  -0.0433   0.7411   0.0107
  -5.250  -0.3395   0.01546   0.00932  -0.0431   0.7324   0.0117
  -5.000  -0.3131   0.01476   0.00843  -0.0428   0.7241   0.0122
  -4.750  -0.2863   0.01419   0.00770  -0.0426   0.7164   0.0126
  -4.250  -0.2346   0.01225   0.00544  -0.0420   0.7016   0.0147
  -3.750  -0.1809   0.01126   0.00423  -0.0415   0.6881   0.0165
  -3.500  -0.1538   0.01089   0.00376  -0.0414   0.6817   0.0173
  -3.250  -0.1264   0.01056   0.00334  -0.0412   0.6754   0.0181
  -3.000  -0.0990   0.01028   0.00297  -0.0411   0.6693   0.0187
  -2.750  -0.0714   0.01005   0.00266  -0.0410   0.6634   0.0194
  -2.500  -0.0437   0.00987   0.00239  -0.0409   0.6574   0.0202
  -2.250  -0.0159   0.00967   0.00210  -0.0408   0.6521   0.0209
  -2.000   0.0120   0.00949   0.00186  -0.0407   0.6462   0.0227
  -1.750   0.0397   0.00933   0.00168  -0.0406   0.6409   0.0285
  -1.500   0.0672   0.00906   0.00153  -0.0406   0.6356   0.0656
  -1.250   0.0947   0.00882   0.00141  -0.0406   0.6301   0.1112
  -1.000   0.1219   0.00856   0.00132  -0.0406   0.6253   0.1723
  -0.750   0.1495   0.00834   0.00126  -0.0406   0.6199   0.2264
  -0.500   0.1766   0.00808   0.00121  -0.0406   0.6146   0.3034
  -0.250   0.2021   0.00752   0.00120  -0.0405   0.6098   0.4778
   0.000   0.2240   0.00673   0.00123  -0.0394   0.6046   0.7176
   0.250   0.2452   0.00627   0.00127  -0.0375   0.5997   0.8794
   0.500   0.2944   0.00619   0.00126  -0.0418   0.5943   0.9759
   0.750   0.3348   0.00622   0.00123  -0.0446   0.5886   0.9978
   1.000   0.3635   0.00628   0.00123  -0.0448   0.5834   1.0000
   1.250   0.3902   0.00632   0.00125  -0.0445   0.5776   1.0000
   1.500   0.4169   0.00640   0.00127  -0.0442   0.5716   1.0000
   1.750   0.4437   0.00645   0.00130  -0.0440   0.5635   1.0000
   2.000   0.4705   0.00652   0.00133  -0.0438   0.5553   1.0000
   2.250   0.4974   0.00659   0.00139  -0.0435   0.5470   1.0000
   2.500   0.5244   0.00667   0.00144  -0.0433   0.5380   1.0000
   2.750   0.5513   0.00676   0.00150  -0.0431   0.5282   1.0000
   3.000   0.5782   0.00686   0.00157  -0.0430   0.5175   1.0000
   3.250   0.6051   0.00696   0.00167  -0.0428   0.5055   1.0000
   3.500   0.6320   0.00707   0.00176  -0.0426   0.4928   1.0000
   3.750   0.6589   0.00720   0.00187  -0.0424   0.4796   1.0000
   4.000   0.6855   0.00735   0.00199  -0.0422   0.4633   1.0000
   4.250   0.7121   0.00753   0.00212  -0.0420   0.4421   1.0000
   4.500   0.7383   0.00776   0.00231  -0.0418   0.4165   1.0000
   4.750   0.7639   0.00807   0.00251  -0.0416   0.3820   1.0000
   5.000   0.7886   0.00852   0.00278  -0.0412   0.3343   1.0000
   5.250   0.8127   0.00907   0.00312  -0.0409   0.2844   1.0000
   5.500   0.8356   0.00980   0.00357  -0.0405   0.2232   1.0000
   5.750   0.8571   0.01072   0.00412  -0.0399   0.1522   1.0000
   6.000   0.8801   0.01139   0.00462  -0.0395   0.1103   1.0000
   6.250   0.9026   0.01210   0.00512  -0.0390   0.0726   1.0000
   6.500   0.9251   0.01278   0.00565  -0.0385   0.0433   1.0000
   6.750   0.9477   0.01342   0.00619  -0.0379   0.0240   1.0000
   7.000   0.9696   0.01414   0.00683  -0.0373   0.0100   1.0000
   7.250   0.9921   0.01478   0.00750  -0.0366   0.0065   1.0000
   7.500   1.0151   0.01532   0.00813  -0.0360   0.0060   1.0000
   7.750   1.0374   0.01591   0.00881  -0.0353   0.0054   1.0000
   8.000   1.0591   0.01653   0.00954  -0.0346   0.0048   1.0000
   8.250   1.0799   0.01722   0.01031  -0.0338   0.0042   1.0000
   8.500   1.0988   0.01812   0.01130  -0.0327   0.0038   1.0000
   8.750   1.1154   0.01919   0.01251  -0.0314   0.0035   1.0000
   9.000   1.1274   0.02068   0.01415  -0.0295   0.0033   1.0000
   9.250   1.1436   0.02162   0.01519  -0.0282   0.0032   1.0000
   9.500   1.1584   0.02264   0.01632  -0.0268   0.0031   1.0000
   9.750   1.1705   0.02383   0.01763  -0.0250   0.0030   1.0000
  10.000   1.1795   0.02505   0.01897  -0.0228   0.0029   1.0000
  10.250   1.1850   0.02641   0.02049  -0.0203   0.0029   1.0000
  10.500   1.1902   0.02791   0.02213  -0.0181   0.0028   1.0000
  10.750   1.1952   0.02958   0.02394  -0.0162   0.0027   1.0000
  11.000   1.1996   0.03140   0.02592  -0.0146   0.0027   1.0000
  11.250   1.2024   0.03353   0.02822  -0.0131   0.0026   1.0000
  11.500   1.2050   0.03573   0.03059  -0.0120   0.0026   1.0000
  11.750   1.2060   0.03819   0.03323  -0.0110   0.0025   1.0000
  12.000   1.2049   0.04098   0.03621  -0.0102   0.0025   1.0000
  12.250   1.2021   0.04406   0.03949  -0.0098   0.0025   1.0000
  12.500   1.1975   0.04744   0.04307  -0.0096   0.0025   1.0000
  12.750   1.1909   0.05119   0.04702  -0.0099   0.0025   1.0000
  13.000   1.1806   0.05561   0.05165  -0.0106   0.0024   1.0000
  13.250   1.1706   0.06018   0.05641  -0.0118   0.0025   1.0000
  13.500   1.1585   0.06528   0.06170  -0.0136   0.0025   1.0000
  13.750   1.1440   0.07104   0.06765  -0.0159   0.0024   1.0000
  14.000   1.1276   0.07761   0.07441  -0.0190   0.0024   1.0000
  14.250   1.1120   0.08453   0.08150  -0.0227   0.0025   1.0000
  14.500   1.0947   0.09240   0.08953  -0.0271   0.0025   1.0000
  14.750   1.0781   0.10075   0.09804  -0.0321   0.0025   1.0000
  15.000   1.0593   0.11031   0.10776  -0.0378   0.0025   1.0000
  15.250   1.0400   0.12078   0.11836  -0.0440   0.0026   1.0000
  15.500   1.0204   0.13200   0.12971  -0.0504   0.0026   1.0000
  15.750   0.9951   0.14583   0.14365  -0.0579   0.0026   1.0000
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