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EPPLER 550 AIRFOIL (e550-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 550 AIRFOIL (e550-il)
Reynolds number: 50,000
Max Cl/Cd: 12.64 at α=-2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e550-il-50000.txt
Download as CSV file: xf-e550-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 550 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  -0.4047   0.11223   0.10563  -0.0435   1.0000   0.1601
 -11.250  -0.5195   0.09025   0.08370  -0.0617   1.0000   0.1134
 -11.000  -0.5051   0.08583   0.07933  -0.0612   1.0000   0.1119
 -10.750  -0.5150   0.08077   0.07431  -0.0621   1.0000   0.1094
 -10.500  -0.5454   0.07549   0.06902  -0.0632   1.0000   0.1066
 -10.250  -0.6096   0.07111   0.06451  -0.0620   1.0000   0.1017
 -10.000  -0.6682   0.07002   0.06317  -0.0567   1.0000   0.0991
  -9.750  -0.6704   0.06648   0.05965  -0.0548   1.0000   0.0981
  -9.500  -0.6834   0.06380   0.05694  -0.0517   1.0000   0.0974
  -9.250  -0.7008   0.06189   0.05499  -0.0476   1.0000   0.0969
  -9.000  -0.7216   0.06070   0.05379  -0.0427   1.0000   0.0963
  -8.750  -0.7442   0.05966   0.05268  -0.0379   1.0000   0.0961
  -8.500  -0.7608   0.05825   0.05114  -0.0339   1.0000   0.0956
  -8.250  -0.7725   0.05658   0.04929  -0.0306   1.0000   0.0955
  -8.000  -0.7794   0.05470   0.04717  -0.0278   1.0000   0.0956
  -7.750  -0.7774   0.05244   0.04455  -0.0262   0.9985   0.0964
  -7.500  -0.7411   0.04885   0.04028  -0.0298   0.9871   0.0981
  -7.250  -0.7007   0.04537   0.03641  -0.0329   0.9767   0.1011
  -7.000  -0.6568   0.04293   0.03384  -0.0361   0.9664   0.1099
  -6.750  -0.6045   0.04059   0.03146  -0.0393   0.9577   0.1236
  -6.500  -0.5543   0.03888   0.02998  -0.0408   0.9487   0.1484
  -6.250  -0.5156   0.03699   0.02854  -0.0417   0.9401   0.1940
  -6.000  -0.5112   0.03443   0.02685  -0.0400   0.9289   0.2595
  -5.750   0.0810   0.05012   0.04213  -0.0672   0.9592   1.0000
  -5.500   0.1253   0.04768   0.03943  -0.0750   0.9462   1.0000
  -5.250   0.1705   0.04544   0.03693  -0.0825   0.9348   1.0000
  -5.000   0.2192   0.04328   0.03451  -0.0903   0.9257   1.0000
  -4.750   0.2582   0.04173   0.03275  -0.0959   0.9136   1.0000
  -4.500   0.2928   0.04053   0.03135  -0.1003   0.9014   1.0000
  -4.250   0.3266   0.03947   0.03011  -0.1042   0.8905   1.0000
  -4.000   0.3549   0.03875   0.02923  -0.1069   0.8795   1.0000
  -3.750   0.3739   0.03856   0.02893  -0.1077   0.8682   1.0000
  -3.500   0.3989   0.03814   0.02838  -0.1094   0.8594   1.0000
  -3.250   0.4143   0.03824   0.02841  -0.1094   0.8490   1.0000
  -3.000   0.4335   0.03823   0.02832  -0.1100   0.8406   1.0000
  -2.750   0.4489   0.03844   0.02847  -0.1100   0.8320   1.0000
  -2.500   0.4663   0.03863   0.02859  -0.1101   0.8250   1.0000
  -2.250   0.4750   0.03928   0.02923  -0.1090   0.8170   1.0000
  -2.000   0.4965   0.03929   0.02917  -0.1095   0.8111   1.0000
  -1.750   0.4955   0.04056   0.03046  -0.1070   0.8033   1.0000
  -1.500   0.5078   0.04114   0.03102  -0.1063   0.7974   1.0000
  -1.250   0.5189   0.04187   0.03173  -0.1054   0.7922   1.0000
  -1.000   0.5086   0.04369   0.03361  -0.1016   0.7854   1.0000
  -0.750   0.4418   0.04718   0.03714  -0.0867   0.7804   0.9800
  -0.500   0.4276   0.04867   0.03863  -0.0816   0.7763   0.9734
  -0.250   0.2886   0.05359   0.04370  -0.0574   0.7739   0.9576
   0.000   0.2274   0.05563   0.04581  -0.0458   0.7726   0.9529
   0.250   0.1951   0.05691   0.04710  -0.0390   0.7725   0.9508
   0.500   0.1710   0.05795   0.04815  -0.0334   0.7733   0.9501
   0.750   0.1546   0.05885   0.04905  -0.0291   0.7746   0.9503
   1.000   0.1436   0.05966   0.04985  -0.0256   0.7761   0.9508
   1.250  -0.2625   0.05403   0.04491   0.0382   1.0000   0.9542
   1.500  -0.2489   0.05425   0.04506   0.0376   1.0000   0.9572
   1.750  -0.2126   0.05574   0.04648   0.0324   0.9934   0.9596
   2.000  -0.1742   0.05732   0.04797   0.0269   0.9833   0.9624
   2.250  -0.1401   0.05870   0.04928   0.0222   0.9718   0.9658
   2.500  -0.1110   0.05991   0.05042   0.0187   0.9591   0.9692
   2.750  -0.0759   0.06131   0.05178   0.0140   0.9455   0.9716
   3.000  -0.0443   0.06261   0.05305   0.0100   0.9319   0.9747
   3.250  -0.0140   0.06401   0.05442   0.0063   0.9184   0.9786
   3.500   0.0177   0.06566   0.05606   0.0024   0.9062   0.9829
   3.750   0.0619   0.06838   0.05876  -0.0039   0.8939   0.9871
   4.000   0.0879   0.06943   0.05981  -0.0066   0.8787   0.9915
   4.250   0.1107   0.07047   0.06086  -0.0089   0.8642   0.9962
   4.500   0.1283   0.07155   0.06194  -0.0102   0.8508   1.0000
   4.750   0.1337   0.07215   0.06254  -0.0090   0.8388   1.0000
   5.000   0.1533   0.07401   0.06439  -0.0099   0.8275   1.0000
   5.250   0.1473   0.07333   0.06370  -0.0067   0.8129   1.0000
   5.500   0.1438   0.07315   0.06351  -0.0040   0.7994   1.0000
   5.750   0.1496   0.07382   0.06416  -0.0031   0.7879   1.0000
   6.000   0.1824   0.07671   0.06705  -0.0065   0.7774   1.0000
   6.250   0.1901   0.07705   0.06739  -0.0064   0.7632   1.0000
   6.500   0.2043   0.07835   0.06870  -0.0074   0.7502   1.0000
   6.750   0.2279   0.08067   0.07104  -0.0099   0.7398   1.0000
   7.000   0.2640   0.08386   0.07427  -0.0140   0.7276   1.0000
   7.250   0.2740   0.08485   0.07527  -0.0146   0.7137   1.0000
   7.500   0.2895   0.08675   0.07720  -0.0162   0.7015   1.0000
   7.750   0.3220   0.09024   0.08072  -0.0198   0.6919   1.0000
   8.000   0.3464   0.09262   0.08316  -0.0221   0.6779   1.0000
   8.250   0.3549   0.09407   0.08464  -0.0228   0.6644   1.0000
   8.500   0.3699   0.09638   0.08699  -0.0243   0.6524   1.0000
   8.750   0.4076   0.10068   0.09136  -0.0281   0.6427   1.0000
   9.000   0.4195   0.10236   0.09308  -0.0290   0.6284   1.0000
   9.250   0.4254   0.10414   0.09489  -0.0295   0.6155   1.0000
   9.500   0.4402   0.10692   0.09773  -0.0310   0.6050   1.0000
   9.750   0.4822   0.11179   0.10267  -0.0344   0.5936   1.0000
  10.000   0.4785   0.11259   0.10352  -0.0341   0.5799   1.0000
  10.250   0.4838   0.11485   0.10582  -0.0347   0.5681   1.0000
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