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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 100,000
Max Cl/Cd: 56.3 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e178-il-100000.txt
Download as CSV file: xf-e178-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3760   0.10954   0.10522  -0.0088   1.0000   0.0829
  -9.500  -0.3866   0.10697   0.10272  -0.0127   1.0000   0.0839
  -9.250  -0.3977   0.10423   0.10005  -0.0167   1.0000   0.0843
  -9.000  -0.3624   0.09717   0.09291  -0.0118   1.0000   0.0892
  -8.750  -0.3592   0.09349   0.08926  -0.0129   1.0000   0.0930
  -8.500  -0.3662   0.09020   0.08604  -0.0160   1.0000   0.0965
  -8.250  -0.3836   0.08746   0.08340  -0.0213   1.0000   0.0977
  -8.000  -0.3624   0.08155   0.07749  -0.0185   1.0000   0.1009
  -7.750  -0.3542   0.07784   0.07381  -0.0186   1.0000   0.1053
  -7.500  -0.3618   0.07434   0.07040  -0.0217   1.0000   0.1096
  -7.250  -0.4318   0.08082   0.07663  -0.0212   1.0000   0.1029
  -7.000  -0.4269   0.07720   0.07305  -0.0248   1.0000   0.1081
  -6.750  -0.4287   0.07202   0.06785  -0.0349   1.0000   0.1129
  -6.500  -0.4137   0.06907   0.06499  -0.0310   1.0000   0.1172
  -6.250  -0.4111   0.06455   0.06032  -0.0397   1.0000   0.1264
  -6.000  -0.3983   0.06161   0.05755  -0.0359   1.0000   0.1305
  -5.750  -0.4078   0.05926   0.05503  -0.0386   1.0000   0.1402
  -5.500  -0.4148   0.05738   0.05332  -0.0337   1.0000   0.1418
  -5.250  -0.4184   0.05587   0.05187  -0.0305   0.9995   0.1453
  -5.000  -0.3820   0.05138   0.04720  -0.0372   0.9893   0.1707
  -4.750  -0.3453   0.04748   0.04313  -0.0426   0.9801   0.1978
  -4.500  -0.2862   0.03292   0.02664  -0.0526   0.9715   0.0797
  -4.250  -0.2454   0.02820   0.02088  -0.0548   0.9631   0.0689
  -4.000  -0.2013   0.02509   0.01717  -0.0578   0.9569   0.0684
  -3.750  -0.1628   0.02293   0.01451  -0.0597   0.9480   0.0729
  -3.500  -0.1193   0.02091   0.01228  -0.0624   0.9419   0.0759
  -3.250  -0.0846   0.01960   0.01081  -0.0633   0.9319   0.0817
  -3.000  -0.0506   0.01836   0.00961  -0.0643   0.9229   0.0943
  -2.750  -0.0177   0.01703   0.00847  -0.0650   0.9147   0.1338
  -2.500   0.0024   0.01501   0.00781  -0.0639   0.9040   0.3868
  -2.250   0.0892   0.01298   0.00740  -0.0719   0.9054   0.9837
  -2.000   0.1303   0.01297   0.00698  -0.0748   0.8959   1.0000
  -1.750   0.1543   0.01311   0.00684  -0.0742   0.8851   1.0000
  -1.500   0.1767   0.01329   0.00679  -0.0732   0.8741   1.0000
  -1.250   0.1987   0.01352   0.00682  -0.0723   0.8633   1.0000
  -1.000   0.2213   0.01375   0.00686  -0.0713   0.8535   1.0000
  -0.750   0.2443   0.01394   0.00685  -0.0702   0.8452   1.0000
  -0.500   0.2669   0.01423   0.00701  -0.0694   0.8351   1.0000
  -0.250   0.2899   0.01449   0.00714  -0.0685   0.8265   1.0000
   0.000   0.3133   0.01473   0.00725  -0.0675   0.8185   1.0000
   0.250   0.3367   0.01506   0.00748  -0.0669   0.8094   1.0000
   0.500   0.3606   0.01529   0.00761  -0.0659   0.8025   1.0000
   0.750   0.3844   0.01564   0.00790  -0.0654   0.7934   1.0000
   1.000   0.4084   0.01596   0.00816  -0.0647   0.7857   1.0000
   1.250   0.4327   0.01625   0.00841  -0.0640   0.7779   1.0000
   1.500   0.4568   0.01663   0.00877  -0.0635   0.7696   1.0000
   1.750   0.4814   0.01688   0.00897  -0.0626   0.7627   1.0000
   2.000   0.5055   0.01732   0.00942  -0.0622   0.7536   1.0000
   2.250   0.5305   0.01751   0.00959  -0.0612   0.7475   1.0000
   2.500   0.5543   0.01795   0.01009  -0.0608   0.7375   1.0000
   2.750   0.5785   0.01830   0.01045  -0.0601   0.7288   1.0000
   3.000   0.6035   0.01845   0.01061  -0.0590   0.7208   1.0000
   3.250   0.6273   0.01884   0.01106  -0.0584   0.7103   1.0000
   3.500   0.6516   0.01910   0.01141  -0.0575   0.7010   1.0000
   3.750   0.6770   0.01914   0.01147  -0.0563   0.6924   1.0000
   4.000   0.7010   0.01939   0.01181  -0.0554   0.6807   1.0000
   4.250   0.7252   0.01954   0.01204  -0.0543   0.6690   1.0000
   4.500   0.7497   0.01959   0.01221  -0.0531   0.6570   1.0000
   4.750   0.7745   0.01954   0.01224  -0.0517   0.6444   1.0000
   5.000   0.7994   0.01943   0.01222  -0.0504   0.6309   1.0000
   5.250   0.8243   0.01927   0.01216  -0.0489   0.6161   1.0000
   5.500   0.8493   0.01901   0.01199  -0.0474   0.5999   1.0000
   5.750   0.8748   0.01860   0.01170  -0.0458   0.5824   1.0000
   6.000   0.8990   0.01829   0.01153  -0.0443   0.5608   1.0000
   6.250   0.9236   0.01785   0.01119  -0.0426   0.5365   1.0000
   6.500   0.9467   0.01751   0.01100  -0.0409   0.5041   1.0000
   6.750   0.9685   0.01725   0.01080  -0.0390   0.4581   1.0000
   7.000   0.9858   0.01751   0.01090  -0.0368   0.3747   1.0000
   7.250   0.9932   0.01923   0.01179  -0.0341   0.2532   1.0000
   7.500   0.9978   0.02164   0.01347  -0.0318   0.1637   1.0000
   7.750   1.0014   0.02421   0.01544  -0.0293   0.1031   1.0000
   8.000   1.0077   0.02664   0.01763  -0.0266   0.0688   1.0000
   8.250   1.0186   0.02882   0.01968  -0.0245   0.0550   1.0000
   8.500   1.0373   0.03134   0.02222  -0.0228   0.0486   1.0000
   8.750   1.0575   0.03344   0.02435  -0.0217   0.0434   1.0000
   9.000   1.0795   0.03647   0.02750  -0.0210   0.0393   1.0000
   9.250   1.1006   0.03929   0.03073  -0.0198   0.0377   1.0000
   9.500   1.1179   0.04266   0.03451  -0.0185   0.0370   1.0000
   9.750   1.1295   0.04634   0.03863  -0.0169   0.0370   1.0000
  10.000   1.1353   0.05025   0.04299  -0.0150   0.0373   1.0000
  10.250   1.1360   0.05430   0.04744  -0.0131   0.0378   1.0000
  10.500   1.1317   0.05841   0.05191  -0.0112   0.0384   1.0000
  10.750   1.1230   0.06236   0.05613  -0.0093   0.0390   1.0000
  11.000   1.1102   0.06629   0.06028  -0.0075   0.0395   1.0000
  11.250   1.0962   0.07073   0.06491  -0.0066   0.0400   1.0000
  11.500   1.0936   0.07588   0.07020  -0.0064   0.0412   1.0000
  11.750   1.0739   0.07877   0.07335  -0.0065   0.0418   1.0000
  12.000   1.0438   0.08381   0.07867  -0.0087   0.0425   1.0000
  12.250   1.0119   0.09053   0.08561  -0.0129   0.0429   1.0000
  12.500   0.9767   0.09941   0.09467  -0.0193   0.0435   1.0000
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