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EPPLER 379 AIRFOIL (e379-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 379 AIRFOIL (e379-il)
Reynolds number: 100,000
Max Cl/Cd: 66.77 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e379-il-100000-n5.txt
Download as CSV file: xf-e379-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 379 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3733   0.13875   0.13416   0.0118   1.0000   0.0075
 -10.250  -0.3630   0.13326   0.12868   0.0110   1.0000   0.0076
 -10.000  -0.3537   0.12905   0.12450   0.0100   1.0000   0.0077
  -9.750  -0.3445   0.12555   0.12103   0.0088   1.0000   0.0078
  -9.500  -0.3355   0.12229   0.11781   0.0076   1.0000   0.0079
  -9.250  -0.3265   0.11917   0.11466   0.0063   1.0000   0.0081
  -9.000  -0.3173   0.11633   0.11186   0.0049   1.0000   0.0082
  -8.750  -0.3081   0.11350   0.10908   0.0036   1.0000   0.0083
  -8.500  -0.2989   0.11074   0.10637   0.0022   1.0000   0.0084
  -8.250  -0.2897   0.10812   0.10381   0.0009   1.0000   0.0086
  -8.000  -0.2802   0.10558   0.10132  -0.0005   1.0000   0.0087
  -7.750  -0.2711   0.10303   0.09884  -0.0019   1.0000   0.0089
  -7.500  -0.2615   0.10062   0.09650  -0.0034   1.0000   0.0090
  -7.250  -0.2505   0.09808   0.09403  -0.0052   1.0000   0.0092
  -7.000  -0.2379   0.09548   0.09150  -0.0075   1.0000   0.0094
  -6.750  -0.2149   0.09224   0.08826  -0.0124   0.9357   0.0096
  -6.500  -0.1916   0.08906   0.08500  -0.0169   0.8913   0.0099
  -6.250  -0.1750   0.08647   0.08232  -0.0193   0.8570   0.0102
  -6.000  -0.1597   0.08408   0.07983  -0.0212   0.8303   0.0104
  -5.750  -0.1438   0.08164   0.07731  -0.0232   0.8076   0.0107
  -5.500  -0.1267   0.07925   0.07475  -0.0254   0.7884   0.0110
  -5.250  -0.1079   0.07671   0.07213  -0.0279   0.7720   0.0114
  -5.000  -0.0876   0.07418   0.06953  -0.0306   0.7568   0.0118
  -4.750  -0.0658   0.07166   0.06693  -0.0335   0.7435   0.0123
  -4.500  -0.0420   0.06918   0.06436  -0.0367   0.7311   0.0133
  -4.250  -0.0140   0.06699   0.06208  -0.0405   0.7196   0.0141
  -4.000   0.0177   0.06516   0.06012  -0.0449   0.7091   0.0145
  -3.750   0.0538   0.06358   0.05840  -0.0501   0.6987   0.0146
  -3.500   0.0875   0.06155   0.05625  -0.0545   0.6890   0.0147
  -3.250   0.1062   0.05755   0.05223  -0.0556   0.6809   0.0149
  -3.000   0.1274   0.05404   0.04866  -0.0572   0.6725   0.0155
  -2.750   0.1570   0.05140   0.04592  -0.0603   0.6644   0.0163
  -2.500   0.1887   0.04903   0.04343  -0.0634   0.6570   0.0172
  -2.250   0.2227   0.04682   0.04111  -0.0667   0.6490   0.0183
  -2.000   0.2600   0.04513   0.03923  -0.0701   0.6424   0.0194
  -1.750   0.3055   0.04455   0.03844  -0.0743   0.6344   0.0201
  -1.500   0.3299   0.04120   0.03500  -0.0758   0.6286   0.0207
  -1.250   0.3577   0.03865   0.03231  -0.0776   0.6213   0.0221
  -1.000   0.3900   0.03685   0.03034  -0.0795   0.6156   0.0239
  -0.750   0.4248   0.03536   0.02871  -0.0816   0.6087   0.0261
  -0.500   0.4672   0.03528   0.02830  -0.0835   0.6028   0.0279
  -0.250   0.4932   0.03243   0.02541  -0.0849   0.5968   0.0291
   0.000   0.5224   0.03072   0.02357  -0.0859   0.5910   0.0322
   0.250   0.5615   0.03071   0.02322  -0.0869   0.5855   0.0374
   0.500   0.5871   0.02826   0.02074  -0.0879   0.5795   0.0404
   0.750   0.6218   0.02780   0.01997  -0.0883   0.5747   0.0478
   1.000   0.6525   0.02646   0.01840  -0.0889   0.5687   0.0480
   1.250   0.6826   0.02459   0.01629  -0.0891   0.5637   0.0227
   1.500   0.7154   0.02401   0.01539  -0.0889   0.5589   0.0279
   1.750   0.7439   0.02343   0.01467  -0.0892   0.5530   0.0469
   2.000   0.7733   0.02197   0.01296  -0.0891   0.5485   0.0357
   2.250   0.8030   0.02097   0.01175  -0.0890   0.5433   0.0327
   2.500   0.8330   0.02007   0.01057  -0.0888   0.5381   0.0322
   2.750   0.8618   0.01926   0.00942  -0.0883   0.5340   0.0348
   3.000   0.8928   0.01882   0.00871  -0.0887   0.5281   0.0471
   3.250   0.9212   0.01832   0.00799  -0.0885   0.5231   0.0482
   3.500   0.9476   0.01814   0.00763  -0.0881   0.5187   0.0503
   3.750   0.9741   0.01819   0.00766  -0.0879   0.5126   0.0546
   4.000   1.0007   0.01824   0.00764  -0.0876   0.5079   0.0740
   4.500   1.0590   0.01776   0.00817  -0.0887   0.4966   1.0000
   4.750   1.0848   0.01802   0.00831  -0.0883   0.4922   1.0000
   5.000   1.1105   0.01837   0.00872  -0.0881   0.4854   1.0000
   5.250   1.1361   0.01862   0.00905  -0.0877   0.4803   1.0000
   5.500   1.1615   0.01896   0.00947  -0.0875   0.4734   1.0000
   5.750   1.1869   0.01920   0.00971  -0.0871   0.4671   1.0000
   6.000   1.2120   0.01951   0.01013  -0.0868   0.4593   1.0000
   6.250   1.2372   0.01970   0.01034  -0.0863   0.4525   1.0000
   6.500   1.2620   0.02002   0.01084  -0.0859   0.4436   1.0000
   6.750   1.2870   0.02024   0.01116  -0.0855   0.4358   1.0000
   7.000   1.3117   0.02046   0.01152  -0.0850   0.4268   1.0000
   7.250   1.3360   0.02074   0.01242  -0.0845   0.4163   1.0000
   7.500   1.3596   0.02064   0.01242  -0.0836   0.3968   1.0000
   7.750   1.3782   0.02064   0.01213  -0.0824   0.3173   1.0000
   8.000   1.3899   0.02249   0.01325  -0.0813   0.2050   1.0000
   8.250   1.3952   0.02553   0.01559  -0.0802   0.1067   1.0000
   8.500   1.3875   0.02988   0.01898  -0.0784   0.0088   1.0000
   8.750   1.3981   0.03163   0.02090  -0.0769   0.0060   1.0000
   9.000   1.4081   0.03331   0.02286  -0.0755   0.0056   1.0000
   9.250   1.4147   0.03519   0.02503  -0.0738   0.0053   1.0000
   9.500   1.4164   0.03724   0.02735  -0.0720   0.0051   1.0000
   9.750   1.4145   0.03966   0.03002  -0.0704   0.0050   1.0000
  10.000   1.4116   0.04250   0.03311  -0.0694   0.0050   1.0000
  10.250   1.4078   0.04571   0.03656  -0.0689   0.0049   1.0000
  10.500   1.4041   0.04908   0.04016  -0.0688   0.0049   1.0000
  10.750   1.3986   0.05283   0.04414  -0.0688   0.0048   1.0000
  11.000   1.3934   0.05664   0.04816  -0.0689   0.0048   1.0000
  11.250   1.3875   0.06064   0.05238  -0.0691   0.0048   1.0000
  11.500   1.3816   0.06471   0.05663  -0.0693   0.0047   1.0000
  11.750   1.3767   0.06867   0.06079  -0.0695   0.0048   1.0000
  12.000   1.3720   0.07267   0.06497  -0.0696   0.0048   1.0000
  12.250   1.3685   0.07656   0.06904  -0.0696   0.0048   1.0000
  12.500   1.3660   0.08038   0.07305  -0.0695   0.0048   1.0000
  12.750   1.3639   0.08435   0.07749  -0.0692   0.0048   1.0000
  13.000   1.3617   0.08846   0.08182  -0.0693   0.0048   1.0000
  13.250   1.3581   0.09295   0.08654  -0.0698   0.0048   1.0000
  13.500   1.3530   0.09787   0.09170  -0.0707   0.0049   1.0000
  13.750   1.3463   0.10327   0.09735  -0.0723   0.0049   1.0000
  14.000   1.3383   0.10904   0.10336  -0.0744   0.0050   1.0000
  14.250   1.3291   0.11527   0.10981  -0.0771   0.0050   1.0000
  14.500   1.3194   0.12185   0.11662  -0.0802   0.0050   1.0000
  14.750   1.3093   0.12878   0.12375  -0.0838   0.0050   1.0000
  15.000   1.2991   0.13604   0.13120  -0.0879   0.0051   1.0000
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