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EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 417 AIRFOIL (e417-il)
Reynolds number: 200,000
Max Cl/Cd: 65.62 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e417-il-200000.txt
Download as CSV file: xf-e417-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4932   0.10137   0.09836  -0.0444   1.0000   0.0647
 -10.250  -0.5181   0.09517   0.09214  -0.0468   1.0000   0.0647
 -10.000  -0.5462   0.08960   0.08655  -0.0483   1.0000   0.0647
  -9.750  -0.5749   0.08472   0.08162  -0.0490   1.0000   0.0647
  -9.500  -0.5990   0.08038   0.07726  -0.0486   1.0000   0.0647
  -9.250  -0.6285   0.07671   0.07354  -0.0473   1.0000   0.0646
  -9.000  -0.6579   0.07365   0.07045  -0.0448   1.0000   0.0645
  -8.750  -0.6862   0.07057   0.06728  -0.0431   1.0000   0.0645
  -8.500  -0.7093   0.06763   0.06418  -0.0418   1.0000   0.0647
  -8.250  -0.7285   0.06506   0.06134  -0.0406   1.0000   0.0649
  -8.000  -0.7762   0.06896   0.06467  -0.0420   1.0000   0.0649
  -7.750  -0.7757   0.05985   0.05574  -0.0426   1.0000   0.0671
  -6.500  -0.6978   0.03708   0.03074  -0.0422   1.0000   0.0397
  -6.250  -0.6713   0.03277   0.02562  -0.0418   1.0000   0.0327
  -6.000  -0.6484   0.03159   0.02426  -0.0412   1.0000   0.0319
  -5.750  -0.6263   0.02927   0.02180  -0.0406   1.0000   0.0314
  -5.500  -0.6040   0.02772   0.02011  -0.0399   1.0000   0.0311
  -5.250  -0.5815   0.02653   0.01880  -0.0391   1.0000   0.0312
  -5.000  -0.5564   0.02561   0.01780  -0.0389   0.9995   0.0315
  -4.750  -0.4909   0.02479   0.01700  -0.0466   0.9875   0.0343
  -4.500  -0.4448   0.02410   0.01630  -0.0510   0.9795   0.0365
  -4.250  -0.4031   0.02352   0.01565  -0.0547   0.9757   0.0393
  -4.000  -0.3593   0.02284   0.01487  -0.0588   0.9712   0.0451
  -3.750  -0.2939   0.01975   0.01423  -0.0706   0.9735   0.5284
  -3.500  -0.2688   0.02011   0.01458  -0.0698   0.9660   0.5783
  -3.250  -0.2349   0.02137   0.01581  -0.0702   0.9620   0.6071
  -3.000  -0.2121   0.02209   0.01648  -0.0687   0.9547   0.6266
  -2.750  -0.1920   0.02394   0.01849  -0.0646   0.9494   0.6462
  -2.500  -0.1757   0.02480   0.01938  -0.0611   0.9419   0.6600
  -2.250  -0.1490   0.02547   0.02003  -0.0600   0.9373   0.6673
  -2.000  -0.1059   0.02563   0.02003  -0.0637   0.9350   0.6742
  -1.750  -0.0883   0.02556   0.01993  -0.0617   0.9269   0.6770
  -1.500  -0.0525   0.02566   0.01997  -0.0635   0.9233   0.6808
  -1.250  -0.0074   0.02567   0.01984  -0.0678   0.9213   0.6861
  -1.000   0.0151   0.02544   0.01955  -0.0674   0.9131   0.6895
  -0.750   0.0502   0.02547   0.01956  -0.0689   0.9094   0.6919
  -0.500   0.0914   0.02549   0.01954  -0.0716   0.9072   0.6948
  -0.250   0.1141   0.02531   0.01933  -0.0714   0.8984   0.6987
   0.000   0.1595   0.02509   0.01902  -0.0757   0.8955   0.7032
   0.250   0.1993   0.02498   0.01891  -0.0779   0.8933   0.7052
   0.500   0.2186   0.02488   0.01883  -0.0765   0.8838   0.7077
   0.750   0.2595   0.02464   0.01860  -0.0791   0.8808   0.7105
   1.000   0.2897   0.02445   0.01840  -0.0801   0.8734   0.7139
   1.250   0.3326   0.02410   0.01802  -0.0836   0.8690   0.7181
   1.500   0.3725   0.02372   0.01769  -0.0857   0.8663   0.7201
   1.750   0.3960   0.02359   0.01761  -0.0850   0.8576   0.7223
   2.000   0.4343   0.02322   0.01729  -0.0869   0.8539   0.7251
   2.250   0.4787   0.02269   0.01682  -0.0900   0.8517   0.7284
   2.500   0.5089   0.02235   0.01651  -0.0908   0.8420   0.7320
   2.750   0.5535   0.02155   0.01577  -0.0936   0.8387   0.7344
   3.000   0.5976   0.02072   0.01505  -0.0961   0.8367   0.7366
   3.250   0.6209   0.02040   0.01482  -0.0951   0.8257   0.7394
   3.500   0.6667   0.01939   0.01391  -0.0979   0.8232   0.7425
   3.750   0.6968   0.01885   0.01346  -0.0981   0.8126   0.7458
   4.000   0.7453   0.01769   0.01240  -0.1015   0.8086   0.7486
   4.250   0.7726   0.01713   0.01195  -0.1008   0.7958   0.7510
   4.500   0.8050   0.01648   0.01143  -0.1010   0.7818   0.7538
   4.750   0.8471   0.01568   0.01072  -0.1031   0.7646   0.7568
   5.000   0.8866   0.01514   0.01022  -0.1050   0.7375   0.7600
   5.250   0.9340   0.01467   0.00968  -0.1084   0.6949   0.7630
   5.500   0.9666   0.01473   0.00942  -0.1087   0.6234   0.7654
   5.750   0.9799   0.01531   0.00964  -0.1057   0.5535   0.7683
   6.000   0.9880   0.01603   0.01005  -0.1020   0.4888   0.7715
   6.250   0.9961   0.01684   0.01055  -0.0986   0.4268   0.7748
   6.500   1.0042   0.01777   0.01114  -0.0955   0.3623   0.7780
   6.750   1.0106   0.01868   0.01176  -0.0920   0.3015   0.7806
   7.000   1.0191   0.01967   0.01245  -0.0891   0.2426   0.7837
   7.250   1.0307   0.02068   0.01320  -0.0868   0.1899   0.7873
   7.500   1.0419   0.02199   0.01413  -0.0848   0.1232   0.7909
   7.750   1.0436   0.02424   0.01574  -0.0812   0.0479   0.7935
   8.000   1.0546   0.02545   0.01696  -0.0787   0.0377   0.7963
   8.250   1.0664   0.02664   0.01823  -0.0764   0.0334   0.7994
   8.500   1.0803   0.02774   0.01943  -0.0746   0.0307   0.8032
   8.750   1.0934   0.02910   0.02083  -0.0729   0.0288   0.8071
   9.000   1.1011   0.03080   0.02262  -0.0703   0.0276   0.8099
   9.250   1.1160   0.03222   0.02414  -0.0686   0.0268   0.8132
   9.500   1.1349   0.03364   0.02568  -0.0675   0.0262   0.8168
   9.750   1.1583   0.03524   0.02739  -0.0672   0.0256   0.8205
  10.000   1.1836   0.03695   0.02925  -0.0670   0.0251   0.8239
  10.250   1.2072   0.03868   0.03116  -0.0665   0.0244   0.8277
  10.500   1.2275   0.04033   0.03299  -0.0659   0.0234   0.8321
  10.750   1.2473   0.04225   0.03507  -0.0654   0.0227   0.8365
  11.000   1.2663   0.04468   0.03778  -0.0645   0.0226   0.8401
  11.250   1.2816   0.04757   0.04101  -0.0631   0.0226   0.8441
  11.500   1.2865   0.05112   0.04502  -0.0607   0.0230   0.8482
  11.750   1.2813   0.05515   0.04953  -0.0573   0.0236   0.8520
  12.000   1.2703   0.05928   0.05409  -0.0537   0.0243   0.8557
  12.250   1.2565   0.06357   0.05875  -0.0505   0.0249   0.8598
  12.500   1.2405   0.06805   0.06354  -0.0479   0.0254   0.8640
  12.750   1.2225   0.07265   0.06841  -0.0458   0.0258   0.8677
  13.000   1.2033   0.07756   0.07357  -0.0443   0.0262   0.8716
  13.250   1.1836   0.08312   0.07934  -0.0438   0.0267   0.8756
  14.500   0.8888   0.11575   0.11329  -0.0536   0.0268   0.8442
  14.750   0.8707   0.12286   0.12049  -0.0577   0.0275   0.8449
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