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EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 417 AIRFOIL (e417-il)
Reynolds number: 100,000
Max Cl/Cd: 46 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e417-il-100000-n5.txt
Download as CSV file: xf-e417-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 417 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.5487   0.10526   0.10029  -0.0481   1.0000   0.0232
 -11.250  -0.5602   0.09966   0.09469  -0.0500   1.0000   0.0229
 -11.000  -0.5786   0.09319   0.08822  -0.0525   1.0000   0.0227
 -10.750  -0.5993   0.08736   0.08235  -0.0546   1.0000   0.0225
 -10.500  -0.6238   0.08189   0.07682  -0.0561   1.0000   0.0224
 -10.250  -0.6459   0.07755   0.07243  -0.0564   1.0000   0.0223
 -10.000  -0.6686   0.07371   0.06851  -0.0560   1.0000   0.0221
  -9.750  -0.6927   0.07032   0.06504  -0.0547   1.0000   0.0220
  -9.500  -0.7166   0.06760   0.06223  -0.0524   1.0000   0.0219
  -9.250  -0.7429   0.06496   0.05948  -0.0498   0.9994   0.0219
  -9.000  -0.7496   0.06077   0.05501  -0.0519   0.9957   0.0217
  -8.750  -0.7497   0.05664   0.05052  -0.0533   0.9919   0.0216
  -8.500  -0.7446   0.05277   0.04626  -0.0542   0.9887   0.0214
  -8.250  -0.7325   0.04912   0.04218  -0.0554   0.9861   0.0214
  -8.000  -0.7188   0.04580   0.03843  -0.0558   0.9832   0.0215
  -7.750  -0.7018   0.04305   0.03528  -0.0561   0.9805   0.0218
  -7.500  -0.6811   0.04065   0.03241  -0.0565   0.9783   0.0227
  -7.250  -0.6566   0.03864   0.02997  -0.0570   0.9763   0.0232
  -7.000  -0.6312   0.03667   0.02781  -0.0576   0.9747   0.0237
  -6.750  -0.6095   0.03507   0.02606  -0.0571   0.9725   0.0241
  -6.500  -0.5878   0.03370   0.02459  -0.0565   0.9700   0.0245
  -6.250  -0.5640   0.03251   0.02332  -0.0562   0.9676   0.0251
  -6.000  -0.5387   0.03146   0.02219  -0.0563   0.9654   0.0257
  -5.750  -0.5120   0.03050   0.02116  -0.0568   0.9635   0.0267
  -5.500  -0.4865   0.02959   0.02015  -0.0571   0.9611   0.0277
  -5.250  -0.4634   0.02876   0.01920  -0.0571   0.9577   0.0294
  -5.000  -0.4366   0.02790   0.01832  -0.0581   0.9550   0.0323
  -4.750  -0.4063   0.02723   0.01755  -0.0595   0.9526   0.0358
  -4.500  -0.3733   0.02649   0.01670  -0.0615   0.9507   0.0411
  -4.250  -0.3421   0.02570   0.01595  -0.0632   0.9483   0.0579
  -4.000  -0.2999   0.02269   0.01467  -0.0706   0.9479   0.3571
  -3.750  -0.2818   0.02339   0.01624  -0.0677   0.9432   0.5527
  -3.250  -0.2328   0.02627   0.01902  -0.0631   0.9361   0.6268
  -3.000  -0.2195   0.02679   0.01949  -0.0594   0.9300   0.6360
  -2.750  -0.1885   0.02683   0.01933  -0.0604   0.9266   0.6435
  -2.500  -0.1574   0.02697   0.01932  -0.0611   0.9238   0.6476
  -2.250  -0.1264   0.02691   0.01910  -0.0624   0.9204   0.6529
  -2.000  -0.0983   0.02674   0.01878  -0.0634   0.9154   0.6579
  -1.750  -0.0686   0.02677   0.01871  -0.0639   0.9117   0.6607
  -1.500  -0.0340   0.02677   0.01861  -0.0656   0.9091   0.6641
  -1.250  -0.0077   0.02666   0.01840  -0.0661   0.9036   0.6684
  -1.000   0.0256   0.02653   0.01815  -0.0681   0.8992   0.6728
  -0.750   0.0582   0.02653   0.01810  -0.0692   0.8959   0.6752
  -0.500   0.0850   0.02650   0.01803  -0.0694   0.8906   0.6780
  -0.250   0.1142   0.02643   0.01793  -0.0702   0.8851   0.6814
   0.000   0.1519   0.02631   0.01774  -0.0727   0.8819   0.6854
   0.250   0.1805   0.02624   0.01763  -0.0735   0.8758   0.6886
   0.500   0.2092   0.02617   0.01757  -0.0738   0.8701   0.6909
   0.750   0.2454   0.02603   0.01744  -0.0756   0.8668   0.6936
   1.000   0.2687   0.02600   0.01742  -0.0753   0.8582   0.6969
   1.250   0.3061   0.02579   0.01721  -0.0775   0.8539   0.7003
   1.500   0.3346   0.02571   0.01714  -0.0781   0.8464   0.7036
   1.750   0.3659   0.02551   0.01701  -0.0788   0.8404   0.7059
   2.000   0.3940   0.02536   0.01692  -0.0790   0.8327   0.7085
   2.250   0.4270   0.02511   0.01673  -0.0801   0.8260   0.7114
   2.500   0.4571   0.02495   0.01664  -0.0808   0.8180   0.7148
   2.750   0.4920   0.02467   0.01642  -0.0824   0.8114   0.7183
   3.000   0.5176   0.02452   0.01638  -0.0819   0.8023   0.7206
   3.250   0.5519   0.02407   0.01605  -0.0828   0.7957   0.7231
   3.500   0.5783   0.02381   0.01590  -0.0825   0.7841   0.7259
   3.750   0.6088   0.02342   0.01561  -0.0828   0.7732   0.7293
   4.000   0.6476   0.02280   0.01511  -0.0845   0.7648   0.7330
   4.250   0.6738   0.02251   0.01496  -0.0839   0.7508   0.7353
   4.500   0.7037   0.02212   0.01471  -0.0839   0.7359   0.7379
   4.750   0.7364   0.02167   0.01440  -0.0843   0.7186   0.7407
   5.000   0.7697   0.02127   0.01410  -0.0850   0.6966   0.7441
   5.250   0.8122   0.02066   0.01355  -0.0871   0.6700   0.7478
   5.500   0.8527   0.02015   0.01309  -0.0886   0.6341   0.7503
   5.750   0.8918   0.01992   0.01278  -0.0901   0.5868   0.7529
   6.000   0.9232   0.02010   0.01280  -0.0905   0.5337   0.7558
   6.250   0.9467   0.02058   0.01312  -0.0897   0.4796   0.7592
   6.500   0.9658   0.02128   0.01359  -0.0884   0.4235   0.7630
   6.750   0.9766   0.02215   0.01418  -0.0856   0.3624   0.7658
   7.000   0.9856   0.02321   0.01489  -0.0827   0.2955   0.7690
   7.250   0.9953   0.02440   0.01570  -0.0803   0.2319   0.7724
   7.500   1.0077   0.02564   0.01661  -0.0786   0.1734   0.7759
   7.750   1.0206   0.02690   0.01756  -0.0769   0.1217   0.7793
   8.000   1.0328   0.02811   0.01859  -0.0750   0.0840   0.7825
   8.250   1.0437   0.02958   0.01984  -0.0729   0.0521   0.7862
   8.500   1.0560   0.03102   0.02124  -0.0711   0.0374   0.7901
   8.750   1.0678   0.03248   0.02272  -0.0692   0.0318   0.7938
   9.000   1.0792   0.03373   0.02419  -0.0671   0.0289   0.7971
   9.250   1.0900   0.03509   0.02570  -0.0651   0.0269   0.8008
   9.500   1.0992   0.03667   0.02739  -0.0631   0.0255   0.8050
   9.750   1.1083   0.03828   0.02916  -0.0611   0.0246   0.8091
  10.000   1.1176   0.03981   0.03089  -0.0591   0.0235   0.8131
  10.250   1.1278   0.04142   0.03266  -0.0574   0.0223   0.8176
  10.500   1.1385   0.04311   0.03447  -0.0560   0.0212   0.8223
  10.750   1.1464   0.04483   0.03633  -0.0543   0.0203   0.8264
  11.000   1.1552   0.04683   0.03843  -0.0527   0.0196   0.8311
  11.250   1.1677   0.04884   0.04067  -0.0515   0.0192   0.8364
  11.500   1.1787   0.05095   0.04302  -0.0501   0.0188   0.8414
  11.750   1.1891   0.05326   0.04560  -0.0487   0.0185   0.8472
  12.000   1.1977   0.05582   0.04844  -0.0474   0.0182   0.8531
  12.250   1.2022   0.05854   0.05147  -0.0458   0.0179   0.8592
  12.500   1.2041   0.06160   0.05483  -0.0444   0.0178   0.8659
  12.750   1.2012   0.06482   0.05841  -0.0427   0.0176   0.8730
  13.250   1.1852   0.07224   0.06648  -0.0400   0.0175   0.8916
  13.500   1.1719   0.07637   0.07094  -0.0391   0.0175   0.9056
  13.750   1.1550   0.08067   0.07554  -0.0384   0.0175   0.9346
  14.000   1.1376   0.08596   0.08113  -0.0394   0.0175   1.0000
  14.250   1.1199   0.09236   0.08781  -0.0419   0.0176   1.0000
  14.500   1.1003   0.09958   0.09530  -0.0455   0.0177   1.0000
  14.750   1.0788   0.10780   0.10375  -0.0504   0.0178   1.0000
  15.000   1.0555   0.11723   0.11342  -0.0566   0.0180   1.0000
  15.250   1.0301   0.12833   0.12468  -0.0645   0.0182   1.0000
  15.500   1.0024   0.14153   0.13803  -0.0739   0.0186   1.0000
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