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EPPLER 549 AIRFOIL (e549-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 549 AIRFOIL (e549-il)
Reynolds number: 50,000
Max Cl/Cd: 4.5 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e549-il-50000.txt
Download as CSV file: xf-e549-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 549 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3165   0.10573   0.09968  -0.0545   1.0000   0.1430
 -11.250  -0.4642   0.09276   0.08622  -0.0659   1.0000   0.1138
 -11.000  -0.4759   0.08755   0.08106  -0.0668   1.0000   0.1109
 -10.750  -0.5186   0.08104   0.07459  -0.0689   1.0000   0.1062
 -10.500  -0.5778   0.07671   0.07026  -0.0683   1.0000   0.1039
 -10.250  -0.6286   0.07529   0.06885  -0.0640   1.0000   0.1028
 -10.000  -0.6749   0.07494   0.06852  -0.0576   1.0000   0.1023
  -9.750  -0.7218   0.07463   0.06809  -0.0511   1.0000   0.1016
  -9.500  -0.7247   0.07153   0.06499  -0.0485   1.0000   0.0999
  -9.250  -0.7391   0.06914   0.06255  -0.0449   1.0000   0.0989
  -9.000  -0.7552   0.06679   0.06011  -0.0413   1.0000   0.0977
  -8.750  -0.7701   0.06435   0.05751  -0.0379   1.0000   0.0965
  -8.500  -0.7829   0.06174   0.05467  -0.0346   1.0000   0.0951
  -8.250  -0.7914   0.05899   0.05162  -0.0315   1.0000   0.0938
  -8.000  -0.7955   0.05624   0.04852  -0.0288   1.0000   0.0926
  -7.750  -0.7947   0.05364   0.04557  -0.0264   1.0000   0.0922
  -7.500  -0.7895   0.05132   0.04296  -0.0243   1.0000   0.0932
  -7.250  -0.7817   0.04917   0.04052  -0.0224   1.0000   0.0956
  -7.000  -0.7712   0.04714   0.03813  -0.0205   1.0000   0.0978
  -6.750  -0.7582   0.04521   0.03577  -0.0187   1.0000   0.1002
  -6.500  -0.7408   0.04307   0.03350  -0.0172   1.0000   0.1033
  -6.250  -0.7239   0.04161   0.03207  -0.0157   1.0000   0.1107
  -6.000  -0.7041   0.04023   0.03067  -0.0139   1.0000   0.1192
  -5.750  -0.6851   0.03920   0.02971  -0.0117   1.0000   0.1323
  -5.500  -0.6699   0.03822   0.02897  -0.0091   1.0000   0.1503
  -5.250  -0.6442   0.03661   0.02782  -0.0092   0.9932   0.1934
  -5.000  -0.6414   0.03263   0.02542  -0.0085   0.9866   0.3048
  -4.750  -0.6313   0.04341   0.03763   0.0119   0.9774   0.6409
  -4.500  -0.3017   0.05971   0.05220  -0.0030   0.9709   0.8182
  -4.250  -0.1733   0.05845   0.05034  -0.0184   0.9652   0.8916
  -3.250   0.0349   0.05375   0.04462  -0.0475   0.9340   0.9673
  -3.000   0.0697   0.05320   0.04389  -0.0519   0.9269   0.9684
  -2.750   0.0639   0.05334   0.04399  -0.0487   0.9165   0.9618
  -2.500   0.0622   0.05372   0.04430  -0.0461   0.9087   0.9556
  -2.250   0.0691   0.05370   0.04422  -0.0451   0.9002   0.9537
  -2.000   0.0833   0.05371   0.04414  -0.0453   0.8931   0.9529
  -1.750   0.0815   0.05396   0.04435  -0.0427   0.8853   0.9511
  -1.500   0.1030   0.05398   0.04427  -0.0440   0.8791   0.9510
  -1.250   0.0809   0.05454   0.04484  -0.0379   0.8723   0.9480
  -1.000   0.0931   0.05473   0.04495  -0.0376   0.8665   0.9479
  -0.750   0.0867   0.05515   0.04535  -0.0342   0.8610   0.9469
  -0.500   0.0712   0.05559   0.04578  -0.0293   0.8565   0.9458
  -0.250   0.0727   0.05591   0.04606  -0.0272   0.8522   0.9458
   0.000   0.0866   0.05626   0.04635  -0.0271   0.8477   0.9465
   0.250   0.0670   0.05668   0.04677  -0.0218   0.8455   0.9466
   0.500   0.0557   0.05707   0.04716  -0.0179   0.8446   0.9472
   0.750   0.0477   0.05745   0.04753  -0.0145   0.8441   0.9484
   1.000   0.0414   0.05784   0.04791  -0.0115   0.8446   0.9499
   1.250   0.0391   0.05837   0.04842  -0.0093   0.8473   0.9515
   1.500  -0.0180   0.05869   0.04883   0.0006   0.8788   0.9539
   1.750  -0.2137   0.05310   0.04351   0.0363   1.0000   0.9607
   2.000  -0.1980   0.05345   0.04382   0.0353   1.0000   0.9640
   2.250  -0.1767   0.05414   0.04446   0.0332   0.9977   0.9679
   2.500  -0.1408   0.05563   0.04589   0.0282   0.9901   0.9712
   2.750  -0.1007   0.05744   0.04767   0.0222   0.9806   0.9743
   3.000  -0.0638   0.05912   0.04932   0.0170   0.9687   0.9775
   3.250  -0.0295   0.06059   0.05077   0.0124   0.9542   0.9811
   3.500   0.0091   0.06241   0.05258   0.0070   0.9403   0.9849
   3.750   0.0486   0.06442   0.05460   0.0015   0.9261   0.9894
   4.000   0.0840   0.06622   0.05641  -0.0032   0.9118   0.9943
   4.250   0.1102   0.06732   0.05754  -0.0063   0.8980   0.9995
   4.500   0.1161   0.06767   0.05790  -0.0053   0.8851   1.0000
   4.750   0.1209   0.06813   0.05836  -0.0041   0.8727   1.0000
   5.000   0.1283   0.06883   0.05907  -0.0033   0.8609   1.0000
   5.250   0.1428   0.07016   0.06040  -0.0037   0.8482   1.0000
   5.500   0.1422   0.06995   0.06020  -0.0015   0.8343   1.0000
   5.750   0.1455   0.07023   0.06048  -0.0004   0.8213   1.0000
   6.000   0.1591   0.07140   0.06167  -0.0012   0.8085   1.0000
   6.250   0.1806   0.07332   0.06359  -0.0034   0.7973   1.0000
   6.500   0.2172   0.07648   0.06677  -0.0078   0.7854   1.0000
   6.750   0.2338   0.07775   0.06807  -0.0092   0.7711   1.0000
   7.000   0.2495   0.07923   0.06959  -0.0106   0.7575   1.0000
   7.250   0.2672   0.08110   0.07149  -0.0124   0.7446   1.0000
   7.500   0.2882   0.08334   0.07377  -0.0146   0.7324   1.0000
   7.750   0.3177   0.08635   0.07684  -0.0179   0.7213   1.0000
   8.000   0.3519   0.08960   0.08015  -0.0215   0.7075   1.0000
   8.250   0.3613   0.09093   0.08152  -0.0221   0.6937   1.0000
   8.500   0.3740   0.09286   0.08350  -0.0232   0.6804   1.0000
   8.750   0.3892   0.09518   0.08587  -0.0246   0.6674   1.0000
   9.000   0.4069   0.09779   0.08854  -0.0263   0.6549   1.0000
   9.250   0.4304   0.10088   0.09170  -0.0284   0.6430   1.0000
   9.500   0.4557   0.10402   0.09490  -0.0305   0.6290   1.0000
   9.750   0.4789   0.10700   0.09797  -0.0322   0.6142   1.0000
  10.000   0.4915   0.10927   0.10031  -0.0330   0.5995   1.0000
  10.250   0.4979   0.11133   0.10243  -0.0335   0.5855   1.0000
  10.500   0.5033   0.11370   0.10486  -0.0340   0.5729   1.0000
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