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E176 (8.83%) (e176-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E176 (8.83%) (e176-il)
Reynolds number: 50,000
Max Cl/Cd: 37.72 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e176-il-50000.txt
Download as CSV file: xf-e176-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4063   0.11013   0.10361  -0.0149   1.0000   0.1914
  -8.500  -0.3871   0.10483   0.09831  -0.0139   1.0000   0.1996
  -8.250  -0.4028   0.10447   0.09812  -0.0169   1.0000   0.2061
  -8.000  -0.3843   0.09960   0.09325  -0.0157   1.0000   0.2186
  -7.750  -0.3741   0.09590   0.08957  -0.0155   1.0000   0.2289
  -7.500  -0.3730   0.09309   0.08687  -0.0159   1.0000   0.2395
  -7.250  -0.3877   0.09231   0.08626  -0.0173   1.0000   0.2491
  -7.000  -0.3790   0.08886   0.08288  -0.0165   1.0000   0.2629
  -6.750  -0.3726   0.08572   0.07982  -0.0159   1.0000   0.2768
  -6.500  -0.3695   0.08285   0.07705  -0.0155   1.0000   0.2911
  -6.250  -0.3685   0.08031   0.07463  -0.0150   1.0000   0.3058
  -6.000  -0.3767   0.07859   0.07307  -0.0149   1.0000   0.3215
  -5.750  -0.3734   0.07565   0.07025  -0.0120   1.0000   0.3372
  -5.500  -0.3724   0.07317   0.06789  -0.0084   1.0000   0.3535
  -5.250  -0.3808   0.07155   0.06640  -0.0045   1.0000   0.3690
  -5.000  -0.3922   0.07020   0.06516  -0.0002   1.0000   0.3846
  -4.750  -0.4031   0.06887   0.06393   0.0040   1.0000   0.4027
  -3.750  -0.3095   0.04355   0.03613  -0.0427   1.0000   0.1349
  -3.500  -0.2906   0.04028   0.03276  -0.0428   1.0000   0.1277
  -3.250  -0.2629   0.03700   0.02869  -0.0440   1.0000   0.1186
  -3.000  -0.2388   0.03471   0.02593  -0.0444   1.0000   0.1182
  -2.750  -0.2137   0.03280   0.02338  -0.0445   1.0000   0.1201
  -2.500  -0.1895   0.03107   0.02122  -0.0443   1.0000   0.1214
  -2.250  -0.1668   0.02949   0.01947  -0.0440   1.0000   0.1246
  -2.000  -0.1434   0.02831   0.01804  -0.0436   1.0000   0.1307
  -1.750  -0.1052   0.02718   0.01672  -0.0456   0.9942   0.1514
  -1.500  -0.0634   0.02576   0.01545  -0.0480   0.9872   0.2197
  -1.250  -0.0221   0.02163   0.01417  -0.0483   0.9821   1.0000
  -1.000   0.0178   0.02236   0.01415  -0.0515   0.9727   1.0000
  -0.750   0.0535   0.02306   0.01432  -0.0540   0.9635   1.0000
  -0.500   0.0929   0.02387   0.01470  -0.0573   0.9548   1.0000
  -0.250   0.1255   0.02459   0.01509  -0.0593   0.9457   1.0000
   0.000   0.1573   0.02534   0.01556  -0.0611   0.9367   1.0000
   0.250   0.1965   0.02620   0.01614  -0.0642   0.9285   1.0000
   0.500   0.2201   0.02691   0.01667  -0.0646   0.9193   1.0000
   0.750   0.2521   0.02776   0.01734  -0.0664   0.9109   1.0000
   1.000   0.2817   0.02859   0.01803  -0.0678   0.9023   1.0000
   1.250   0.3061   0.02944   0.01876  -0.0683   0.8936   1.0000
   1.500   0.3434   0.03038   0.01960  -0.0709   0.8856   1.0000
   1.750   0.3599   0.03126   0.02041  -0.0702   0.8764   1.0000
   2.000   0.3881   0.03223   0.02133  -0.0713   0.8681   1.0000
   2.250   0.4158   0.03320   0.02226  -0.0723   0.8592   1.0000
   2.500   0.4350   0.03423   0.02326  -0.0721   0.8501   1.0000
   2.750   0.4666   0.03527   0.02430  -0.0736   0.8411   1.0000
   3.000   0.4886   0.03633   0.02539  -0.0737   0.8312   1.0000
   3.250   0.5076   0.03746   0.02655  -0.0734   0.8212   1.0000
   3.500   0.5349   0.03857   0.02770  -0.0742   0.8107   1.0000
   3.750   0.5709   0.03960   0.02881  -0.0760   0.8000   1.0000
   4.000   0.5859   0.04082   0.03012  -0.0751   0.7881   1.0000
   4.250   0.6058   0.04202   0.03140  -0.0748   0.7757   1.0000
   4.500   0.6286   0.04321   0.03269  -0.0748   0.7625   1.0000
   4.750   0.6535   0.04434   0.03394  -0.0748   0.7484   1.0000
   5.000   0.6800   0.04540   0.03515  -0.0749   0.7334   1.0000
   5.250   0.7114   0.04626   0.03624  -0.0752   0.7172   1.0000
   5.500   0.7542   0.04664   0.03687  -0.0761   0.7002   1.0000
   5.750   0.7645   0.04800   0.03835  -0.0743   0.6815   1.0000
   6.000   0.7963   0.04842   0.03902  -0.0738   0.6616   1.0000
   6.250   0.8410   0.04792   0.03891  -0.0734   0.6407   1.0000
   6.500   0.8770   0.04729   0.03859  -0.0717   0.6179   1.0000
   6.750   0.9141   0.04601   0.03766  -0.0692   0.5938   1.0000
   7.000   0.9688   0.04220   0.03437  -0.0657   0.5676   1.0000
   7.250   1.0211   0.03750   0.03010  -0.0611   0.5355   1.0000
   7.500   1.0687   0.03229   0.02523  -0.0558   0.4905   1.0000
   7.750   1.0936   0.02899   0.02185  -0.0499   0.4181   1.0000
   8.000   1.0950   0.02925   0.02133  -0.0441   0.3186   1.0000
   8.250   1.0869   0.03194   0.02302  -0.0395   0.2360   1.0000
   8.500   1.0784   0.03500   0.02549  -0.0359   0.1760   1.0000
   8.750   1.0803   0.03827   0.02821  -0.0330   0.1303   1.0000
   9.000   1.1093   0.04172   0.03129  -0.0320   0.1010   1.0000
   9.250   1.1471   0.04553   0.03513  -0.0320   0.0884   1.0000
   9.500   1.1653   0.04868   0.03886  -0.0306   0.0823   1.0000
   9.750   1.1907   0.05290   0.04298  -0.0306   0.0765   1.0000
  10.000   1.2000   0.05672   0.04739  -0.0288   0.0755   1.0000
  10.250   1.2053   0.06090   0.05206  -0.0270   0.0752   1.0000
  10.500   1.2056   0.06524   0.05683  -0.0253   0.0753   1.0000
  10.750   1.2025   0.06969   0.06164  -0.0237   0.0756   1.0000
  11.000   1.1968   0.07428   0.06651  -0.0224   0.0760   1.0000
  11.250   1.1917   0.07925   0.07169  -0.0213   0.0765   1.0000
  11.500   1.1602   0.08198   0.07481  -0.0192   0.0774   1.0000
  11.750   1.1144   0.08666   0.07983  -0.0201   0.0789   1.0000
  12.000   1.0716   0.09378   0.08719  -0.0239   0.0807   1.0000
  12.250   1.0339   0.10257   0.09611  -0.0296   0.0829   1.0000
  12.500   1.0034   0.11222   0.10575  -0.0358   0.0853   1.0000
  12.750   0.9879   0.12060   0.11413  -0.0402   0.0874   1.0000
  13.000   0.9826   0.12772   0.12124  -0.0431   0.0886   1.0000
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