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EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 856 AIRFOIL (e856-il)
Reynolds number: 50,000
Max Cl/Cd: 4.61 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e856-il-50000.txt
Download as CSV file: xf-e856-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 856 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2798   0.12678   0.12066  -0.0329   1.0000   0.2917
  -9.750  -0.2596   0.12191   0.11582  -0.0313   1.0000   0.2978
  -9.500  -0.4020   0.10360   0.09795  -0.0471   1.0000   0.1475
  -9.250  -0.3981   0.10221   0.09662  -0.0434   1.0000   0.1491
  -9.000  -0.3987   0.10169   0.09618  -0.0396   1.0000   0.1528
  -8.750  -0.5886   0.08453   0.07927  -0.0505   1.0000   0.1171
  -8.500  -0.6070   0.08170   0.07648  -0.0488   1.0000   0.1165
  -8.250  -0.6256   0.07873   0.07353  -0.0475   1.0000   0.1157
  -8.000  -0.6461   0.07525   0.07000  -0.0467   1.0000   0.1147
  -7.750  -0.6658   0.07120   0.06582  -0.0465   1.0000   0.1136
  -7.500  -0.6811   0.06688   0.06124  -0.0467   1.0000   0.1130
  -7.250  -0.6649   0.06016   0.05378  -0.0537   0.9900   0.1141
  -7.000  -0.6401   0.05463   0.04728  -0.0591   0.9796   0.1165
  -6.750  -0.6064   0.05160   0.04423  -0.0623   0.9694   0.1240
  -6.500  -0.5736   0.04813   0.03993  -0.0660   0.9596   0.1325
  -6.250  -0.5390   0.04584   0.03747  -0.0686   0.9494   0.1460
  -6.000  -0.5083   0.04383   0.03530  -0.0703   0.9386   0.1618
  -5.750  -0.4779   0.04207   0.03364  -0.0715   0.9285   0.1823
  -5.500  -0.4408   0.04052   0.03219  -0.0738   0.9196   0.2137
  -5.250  -0.4152   0.03942   0.03144  -0.0741   0.9091   0.2505
  -5.000  -0.3894   0.03896   0.03139  -0.0741   0.8991   0.3057
  -4.750  -0.3543   0.04068   0.03369  -0.0733   0.8897   0.3850
  -4.500  -0.3428   0.04260   0.03579  -0.0688   0.8784   0.4316
  -4.250  -0.3222   0.04452   0.03769  -0.0653   0.8689   0.4783
  -4.000  -0.3032   0.04615   0.03928  -0.0617   0.8598   0.5135
  -3.750  -0.2916   0.04752   0.04065  -0.0570   0.8513   0.5383
  -3.500  -0.2724   0.04835   0.04136  -0.0543   0.8430   0.5678
  -3.250  -0.2614   0.04915   0.04207  -0.0504   0.8353   0.5897
  -3.000  -0.2482   0.04963   0.04244  -0.0476   0.8277   0.6128
  -2.750  -0.2266   0.04998   0.04263  -0.0460   0.8214   0.6369
  -2.500  -0.2248   0.05031   0.04289  -0.0427   0.8140   0.6537
  -2.250  -0.2031   0.05058   0.04304  -0.0407   0.8078   0.6740
  -2.000  -0.1970   0.05087   0.04323  -0.0383   0.8020   0.6901
  -1.750  -0.1894   0.05112   0.04338  -0.0365   0.7966   0.7055
  -1.500  -0.1664   0.05124   0.04335  -0.0361   0.7911   0.7223
  -1.250  -0.1558   0.05155   0.04356  -0.0344   0.7861   0.7350
  -1.000  -0.1520   0.05190   0.04385  -0.0324   0.7821   0.7455
  -0.750  -0.1378   0.05226   0.04409  -0.0324   0.7786   0.7576
  -0.500  -0.1158   0.05260   0.04431  -0.0328   0.7745   0.7692
  -0.250  -0.0959   0.05305   0.04463  -0.0329   0.7704   0.7801
   0.000  -0.0884   0.05373   0.04521  -0.0328   0.7685   0.7901
   0.250  -0.0803   0.05443   0.04587  -0.0317   0.7684   0.7996
   0.500  -0.0683   0.05524   0.04660  -0.0318   0.7685   0.8100
   0.750  -0.0555   0.05613   0.04741  -0.0319   0.7692   0.8208
   1.000  -0.0368   0.05720   0.04841  -0.0326   0.7714   0.8325
   1.250  -0.1690   0.05813   0.04981  -0.0191   0.9128   0.8299
   1.500  -0.1363   0.05996   0.05152  -0.0219   0.9060   0.8449
   1.750  -0.1244   0.05999   0.05149  -0.0215   0.8989   0.8581
   2.000  -0.0971   0.06130   0.05275  -0.0234   0.8919   0.8756
   2.250  -0.0783   0.06208   0.05352  -0.0241   0.8853   0.8937
   2.500  -0.0424   0.06366   0.05511  -0.0279   0.8755   0.9189
   2.750  -0.0101   0.06481   0.05628  -0.0323   0.8661   0.9501
   3.000   0.0366   0.06730   0.05865  -0.0396   0.8576   1.0000
   3.250   0.0537   0.06790   0.05913  -0.0416   0.8476   1.0000
   3.500   0.1018   0.07130   0.06232  -0.0488   0.8405   1.0000
   3.750   0.1160   0.07180   0.06270  -0.0502   0.8295   1.0000
   4.000   0.1606   0.07531   0.06601  -0.0563   0.8235   1.0000
   4.250   0.1710   0.07579   0.06638  -0.0567   0.8125   1.0000
   4.500   0.2144   0.07954   0.06994  -0.0619   0.8063   1.0000
   4.750   0.2208   0.07982   0.07013  -0.0613   0.7945   1.0000
   5.000   0.2604   0.08361   0.07375  -0.0655   0.7892   1.0000
   5.250   0.2630   0.08375   0.07383  -0.0642   0.7775   1.0000
   5.500   0.3033   0.08782   0.07776  -0.0681   0.7719   1.0000
   5.750   0.3032   0.08778   0.07768  -0.0664   0.7597   1.0000
   6.000   0.3415   0.09189   0.08169  -0.0698   0.7547   1.0000
   6.250   0.3393   0.09179   0.08157  -0.0679   0.7427   1.0000
   6.500   0.3772   0.09602   0.08571  -0.0711   0.7374   1.0000
   6.750   0.3748   0.09596   0.08564  -0.0692   0.7251   1.0000
   7.000   0.4083   0.09997   0.08960  -0.0718   0.7200   1.0000
   7.250   0.4083   0.10020   0.08983  -0.0704   0.7077   1.0000
   7.500   0.4322   0.10346   0.09306  -0.0718   0.7019   1.0000
   7.750   0.4402   0.10455   0.09416  -0.0713   0.6903   1.0000
   8.000   0.4599   0.10756   0.09717  -0.0724   0.6843   1.0000
   8.250   0.4722   0.10910   0.09873  -0.0724   0.6726   1.0000
   8.500   0.4848   0.11160   0.10123  -0.0727   0.6659   1.0000
   8.750   0.5021   0.11373   0.10337  -0.0733   0.6551   1.0000
   9.000   0.5098   0.11583   0.10550  -0.0732   0.6469   1.0000
   9.250   0.5321   0.11860   0.10830  -0.0743   0.6374   1.0000
   9.500   0.5357   0.12043   0.11016  -0.0740   0.6287   1.0000
   9.750   0.5617   0.12366   0.11343  -0.0753   0.6198   1.0000
  10.000   0.5613   0.12513   0.11495  -0.0748   0.6099   1.0000
  10.250   0.5910   0.12900   0.11887  -0.0764   0.6021   1.0000
  10.500   0.5870   0.13005   0.11997  -0.0758   0.5913   1.0000
  10.750   0.6219   0.13483   0.12482  -0.0778   0.5844   1.0000
  11.000   0.6125   0.13516   0.12519  -0.0768   0.5728   1.0000
  11.250   0.6447   0.14018   0.13029  -0.0787   0.5666   1.0000
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