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EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 417 AIRFOIL (e417-il)
Reynolds number: 50,000
Max Cl/Cd: 30.21 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e417-il-50000-n5.txt
Download as CSV file: xf-e417-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5277   0.10765   0.10068  -0.0482   1.0000   0.0425
 -10.500  -0.5471   0.10038   0.09346  -0.0512   1.0000   0.0416
 -10.250  -0.5728   0.09341   0.08650  -0.0540   1.0000   0.0407
 -10.000  -0.6041   0.08719   0.08025  -0.0559   1.0000   0.0400
  -9.750  -0.6382   0.08210   0.07507  -0.0563   1.0000   0.0394
  -9.500  -0.6752   0.07829   0.07113  -0.0550   1.0000   0.0388
  -9.250  -0.7070   0.07536   0.06809  -0.0525   1.0000   0.0385
  -9.000  -0.7270   0.07207   0.06459  -0.0511   1.0000   0.0382
  -8.750  -0.7395   0.06879   0.06106  -0.0496   1.0000   0.0380
  -8.500  -0.7457   0.06545   0.05740  -0.0483   1.0000   0.0378
  -8.250  -0.7468   0.06207   0.05375  -0.0472   1.0000   0.0377
  -8.000  -0.7446   0.05867   0.05002  -0.0462   1.0000   0.0378
  -7.750  -0.7379   0.05549   0.04650  -0.0454   1.0000   0.0377
  -7.250  -0.7147   0.04952   0.03988  -0.0438   1.0000   0.0381
  -7.000  -0.6993   0.04690   0.03700  -0.0429   1.0000   0.0385
  -6.750  -0.6827   0.04469   0.03458  -0.0420   1.0000   0.0395
  -6.500  -0.6652   0.04292   0.03264  -0.0410   1.0000   0.0412
  -6.250  -0.6467   0.04136   0.03090  -0.0398   1.0000   0.0430
  -6.000  -0.6276   0.03999   0.02933  -0.0381   1.0000   0.0449
  -5.750  -0.6086   0.03887   0.02802  -0.0358   1.0000   0.0465
  -5.500  -0.5903   0.03801   0.02697  -0.0332   1.0000   0.0478
  -5.250  -0.5741   0.03706   0.02595  -0.0306   1.0000   0.0496
  -5.000  -0.5582   0.03605   0.02492  -0.0290   1.0000   0.0521
  -4.750  -0.5410   0.03505   0.02382  -0.0278   1.0000   0.0559
  -4.500  -0.5224   0.03393   0.02262  -0.0273   1.0000   0.0626
  -4.250  -0.5016   0.03270   0.02135  -0.0276   1.0000   0.0737
  -4.000  -0.4762   0.03066   0.01965  -0.0297   1.0000   0.1089
  -3.250  -0.4574   0.03387   0.02570  -0.0114   1.0000   0.6492
  -3.000  -0.4452   0.03511   0.02675  -0.0063   0.9978   0.6756
  -2.750  -0.4217   0.03581   0.02716  -0.0046   0.9930   0.6923
  -2.500  -0.3906   0.03588   0.02691  -0.0061   0.9883   0.7037
  -2.250  -0.3631   0.03602   0.02679  -0.0063   0.9836   0.7104
  -2.000  -0.3301   0.03588   0.02635  -0.0089   0.9787   0.7186
  -1.750  -0.3000   0.03600   0.02624  -0.0099   0.9740   0.7236
  -1.500  -0.2707   0.03584   0.02587  -0.0114   0.9683   0.7294
  -1.250  -0.2362   0.03587   0.02568  -0.0141   0.9634   0.7349
  -1.000  -0.2090   0.03579   0.02544  -0.0148   0.9574   0.7391
  -0.750  -0.1758   0.03582   0.02530  -0.0171   0.9519   0.7442
  -0.500  -0.1423   0.03580   0.02513  -0.0196   0.9462   0.7489
  -0.250  -0.1138   0.03581   0.02503  -0.0205   0.9397   0.7526
   0.000  -0.0820   0.03588   0.02499  -0.0223   0.9338   0.7568
   0.250  -0.0500   0.03588   0.02489  -0.0245   0.9268   0.7613
   0.500  -0.0153   0.03601   0.02493  -0.0268   0.9210   0.7652
   0.750   0.0107   0.03597   0.02486  -0.0273   0.9130   0.7688
   1.000   0.0460   0.03611   0.02494  -0.0298   0.9068   0.7727
   1.250   0.0772   0.03613   0.02493  -0.0317   0.8985   0.7770
   1.500   0.1096   0.03621   0.02499  -0.0334   0.8913   0.7805
   1.750   0.1397   0.03624   0.02504  -0.0346   0.8830   0.7840
   2.000   0.1698   0.03628   0.02509  -0.0359   0.8743   0.7879
   2.250   0.2085   0.03637   0.02520  -0.0389   0.8672   0.7920
   2.500   0.2349   0.03636   0.02526  -0.0394   0.8569   0.7955
   2.750   0.2662   0.03635   0.02530  -0.0407   0.8480   0.7991
   3.000   0.3011   0.03631   0.02534  -0.0426   0.8391   0.8030
   3.250   0.3313   0.03633   0.02545  -0.0439   0.8279   0.8070
   3.500   0.3607   0.03625   0.02548  -0.0447   0.8173   0.8107
   3.750   0.3976   0.03605   0.02540  -0.0465   0.8090   0.8145
   4.000   0.4253   0.03602   0.02550  -0.0471   0.7965   0.8186
   4.250   0.4563   0.03599   0.02563  -0.0483   0.7840   0.8228
   4.500   0.4840   0.03579   0.02559  -0.0484   0.7714   0.8266
   4.750   0.5154   0.03551   0.02548  -0.0490   0.7586   0.8308
   5.000   0.5500   0.03513   0.02531  -0.0502   0.7454   0.8352
   5.250   0.5841   0.03461   0.02500  -0.0509   0.7321   0.8394
   5.500   0.6177   0.03392   0.02454  -0.0512   0.7189   0.8439
   5.750   0.6478   0.03344   0.02430  -0.0512   0.7023   0.8487
   6.000   0.6781   0.03293   0.02403  -0.0512   0.6842   0.8534
   6.250   0.7090   0.03220   0.02355  -0.0507   0.6651   0.8582
   6.500   0.7470   0.03120   0.02282  -0.0511   0.6446   0.8634
   6.750   0.7775   0.03063   0.02246  -0.0507   0.6173   0.8687
   7.000   0.8111   0.02987   0.02188  -0.0504   0.5855   0.8743
   7.250   0.8444   0.02941   0.02154  -0.0503   0.5458   0.8802
   7.500   0.8709   0.02923   0.02137  -0.0492   0.5009   0.8861
   7.750   0.8920   0.02953   0.02161  -0.0477   0.4521   0.8930
   8.000   0.9072   0.03013   0.02212  -0.0457   0.4039   0.9002
   8.250   0.9187   0.03103   0.02291  -0.0434   0.3550   0.9084
   8.500   0.9263   0.03210   0.02385  -0.0408   0.3078   0.9176
   8.750   0.9325   0.03339   0.02499  -0.0385   0.2620   0.9287
   9.000   0.9373   0.03493   0.02635  -0.0363   0.2158   0.9438
   9.500   0.9453   0.03901   0.02981  -0.0337   0.1168   1.0000
   9.750   0.9542   0.04159   0.03214  -0.0333   0.0861   1.0000
  10.000   0.9647   0.04415   0.03470  -0.0328   0.0674   1.0000
  10.250   0.9768   0.04665   0.03725  -0.0324   0.0578   1.0000
  10.500   0.9899   0.04909   0.03973  -0.0321   0.0523   1.0000
  10.750   1.0107   0.05129   0.04218  -0.0320   0.0477   1.0000
  11.000   1.0281   0.05359   0.04463  -0.0320   0.0437   1.0000
  11.250   1.0455   0.05607   0.04716  -0.0321   0.0409   1.0000
  11.500   1.0672   0.05873   0.05025  -0.0321   0.0384   1.0000
  11.750   1.0848   0.06179   0.05365  -0.0321   0.0370   1.0000
  12.000   1.0959   0.06518   0.05737  -0.0318   0.0360   1.0000
  12.250   1.1009   0.06888   0.06139  -0.0315   0.0353   1.0000
  12.500   1.1005   0.07286   0.06569  -0.0312   0.0348   1.0000
  12.750   1.0951   0.07720   0.07034  -0.0310   0.0345   1.0000
  13.000   1.0853   0.08198   0.07542  -0.0313   0.0343   1.0000
  13.250   1.0712   0.08731   0.08105  -0.0323   0.0343   1.0000
  13.500   1.0533   0.09336   0.08740  -0.0342   0.0344   1.0000
  13.750   1.0315   0.10040   0.09472  -0.0373   0.0346   1.0000
  14.000   1.0041   0.10916   0.10375  -0.0424   0.0350   1.0000
  14.250   0.9723   0.12028   0.11510  -0.0499   0.0358   1.0000
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