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lrn1007 (lrn1007-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: lrn1007 (lrn1007-il)
Reynolds number: 500,000
Max Cl/Cd: 150.75 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-lrn1007-il-500000-n5.txt
Download as CSV file: xf-lrn1007-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: lrn1007                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.0997   0.08477   0.08149  -0.0713   0.7874   0.0015
  -7.250  -0.0913   0.08235   0.07909  -0.0726   0.7868   0.0015
  -7.000  -0.0838   0.08009   0.07685  -0.0738   0.7862   0.0015
  -6.750  -0.0730   0.07756   0.07433  -0.0759   0.7856   0.0015
  -6.500  -0.0601   0.07492   0.07169  -0.0785   0.7850   0.0015
  -6.250  -0.0454   0.07219   0.06896  -0.0814   0.7842   0.0015
  -5.750  -0.0113   0.06661   0.06332  -0.0880   0.7822   0.0015
  -1.250   0.4910   0.02127   0.01636  -0.1330   0.7659   0.0023
  -1.000   0.5200   0.01983   0.01478  -0.1334   0.7641   0.0031
  -0.750   0.5501   0.01889   0.01369  -0.1332   0.7623   0.0045
  -0.500   0.5812   0.01896   0.01360  -0.1325   0.7606   0.0052
  -0.250   0.6097   0.01637   0.01080  -0.1331   0.7589   0.0060
   0.250   0.6678   0.01421   0.00835  -0.1327   0.7543   0.0045
   0.500   0.6960   0.01321   0.00724  -0.1326   0.7514   0.0084
   1.500   0.8086   0.01025   0.00401  -0.1317   0.7405   0.0162
   1.750   0.8362   0.00971   0.00343  -0.1314   0.7369   0.0067
   2.250   0.8923   0.00899   0.00247  -0.1313   0.7298   0.0048
   2.500   0.9199   0.00729   0.00261  -0.1320   0.7245   1.0000
   2.750   0.9472   0.00727   0.00257  -0.1321   0.7194   1.0000
   3.000   0.9744   0.00726   0.00256  -0.1322   0.7138   1.0000
   3.250   1.0014   0.00725   0.00256  -0.1323   0.7051   1.0000
   3.500   1.0282   0.00723   0.00257  -0.1324   0.6925   1.0000
   3.750   1.0548   0.00714   0.00242  -0.1323   0.6715   1.0000
   4.000   1.0794   0.00716   0.00225  -0.1318   0.6431   1.0000
   4.250   1.1029   0.00741   0.00234  -0.1313   0.6128   1.0000
   4.500   1.1241   0.00786   0.00257  -0.1304   0.5683   1.0000
   4.750   1.1347   0.00912   0.00323  -0.1278   0.4649   1.0000
   5.000   1.1156   0.01263   0.00499  -0.1210   0.1863   1.0000
   5.250   1.1084   0.01524   0.00656  -0.1160   0.0019   1.0000
   5.500   1.1300   0.01562   0.00703  -0.1151   0.0013   1.0000
   5.750   1.1500   0.01613   0.00767  -0.1139   0.0013   1.0000
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