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E61 (5.64%) (e61-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E61 (5.64%) (e61-il)
Reynolds number: 100,000
Max Cl/Cd: 75.78 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e61-il-100000-n5.txt
Download as CSV file: xf-e61-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E61  (5.64%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3245   0.12656   0.12184  -0.0238   1.0000   0.0197
  -8.500  -0.3247   0.12457   0.11989  -0.0230   1.0000   0.0202
  -8.250  -0.3256   0.12263   0.11800  -0.0222   1.0000   0.0219
  -8.000  -0.3167   0.11990   0.11524  -0.0241   0.9980   0.0228
  -7.750  -0.3024   0.11730   0.11265  -0.0284   0.9945   0.0244
  -7.500  -0.2916   0.11547   0.11084  -0.0324   0.9898   0.0251
  -7.250  -0.2815   0.11404   0.10943  -0.0370   0.9846   0.0254
  -7.000  -0.2759   0.11275   0.10818  -0.0406   0.9777   0.0256
  -6.750  -0.2578   0.10969   0.10513  -0.0463   0.9726   0.0257
  -6.500  -0.2476   0.10273   0.09819  -0.0436   0.9718   0.0268
  -6.250  -0.2377   0.09919   0.09466  -0.0435   0.9672   0.0278
  -6.000  -0.2242   0.09591   0.09140  -0.0456   0.9623   0.0296
  -5.750  -0.2089   0.09277   0.08826  -0.0489   0.9572   0.0312
  -5.500  -0.1945   0.08972   0.08522  -0.0521   0.9507   0.0329
  -5.250  -0.1726   0.08659   0.08209  -0.0585   0.9444   0.0356
  -5.000  -0.1315   0.08365   0.07910  -0.0732   0.9370   0.0371
  -4.750  -0.0972   0.07998   0.07537  -0.0827   0.9311   0.0374
  -4.500  -0.0968   0.07508   0.07055  -0.0788   0.9267   0.0385
  -4.250  -0.0814   0.07160   0.06706  -0.0786   0.9237   0.0406
  -4.000  -0.0601   0.06849   0.06393  -0.0820   0.9179   0.0439
  -3.500   0.0221   0.05990   0.05515  -0.1003   0.9107   0.0547
  -3.250   0.0594   0.05623   0.05139  -0.1069   0.9067   0.0586
  -3.000   0.1438   0.05010   0.04490  -0.1273   0.9045   0.0654
  -2.750   0.1758   0.04659   0.04135  -0.1308   0.9013   0.0671
  -2.500   0.2587   0.03901   0.03324  -0.1461   0.9020   0.0349
  -2.250   0.3314   0.03422   0.02777  -0.1579   0.9023   0.0367
  -2.000   0.3879   0.03069   0.02373  -0.1657   0.9019   0.0358
  -1.750   0.4400   0.02801   0.02050  -0.1717   0.9011   0.0344
  -1.500   0.4870   0.02607   0.01797  -0.1760   0.8998   0.0334
  -1.250   0.5300   0.02461   0.01608  -0.1792   0.8982   0.0329
  -1.000   0.5709   0.02346   0.01463  -0.1818   0.8966   0.0329
  -0.750   0.5998   0.02289   0.01392  -0.1821   0.8907   0.0333
  -0.500   0.6354   0.02228   0.01318  -0.1838   0.8872   0.0344
  -0.250   0.6737   0.02175   0.01247  -0.1858   0.8846   0.0369
   0.000   0.7083   0.02139   0.01206  -0.1872   0.8805   0.0479
   0.250   0.7418   0.02085   0.01189  -0.1887   0.8753   0.1674
   0.500   0.7678   0.01914   0.01186  -0.1882   0.8719   1.0000
   0.750   0.8001   0.01913   0.01161  -0.1889   0.8671   1.0000
   1.000   0.8290   0.01919   0.01151  -0.1890   0.8605   1.0000
   1.250   0.8656   0.01898   0.01116  -0.1905   0.8572   1.0000
   1.500   0.8916   0.01911   0.01121  -0.1901   0.8489   1.0000
   1.750   0.9274   0.01890   0.01095  -0.1914   0.8446   1.0000
   2.000   0.9556   0.01894   0.01095  -0.1913   0.8368   1.0000
   2.250   0.9912   0.01871   0.01069  -0.1926   0.8314   1.0000
   2.500   1.0202   0.01870   0.01069  -0.1926   0.8229   1.0000
   2.750   1.0582   0.01838   0.01044  -0.1942   0.8169   1.0000
   3.000   1.0864   0.01838   0.01049  -0.1940   0.8067   1.0000
   3.250   1.1193   0.01823   0.01039  -0.1947   0.7972   1.0000
   3.500   1.1581   0.01792   0.01014  -0.1964   0.7880   1.0000
   3.750   1.1905   0.01782   0.01011  -0.1969   0.7756   1.0000
   4.000   1.2228   0.01772   0.01018  -0.1974   0.7617   1.0000
   4.250   1.2511   0.01774   0.01030  -0.1971   0.7452   1.0000
   4.500   1.2797   0.01776   0.01042  -0.1968   0.7262   1.0000
   4.750   1.3102   0.01775   0.01049  -0.1969   0.7049   1.0000
   5.000   1.3380   0.01783   0.01065  -0.1964   0.6796   1.0000
   5.250   1.3620   0.01803   0.01100  -0.1952   0.6485   1.0000
   5.500   1.3861   0.01829   0.01126  -0.1939   0.6093   1.0000
   5.750   1.4076   0.01871   0.01160  -0.1922   0.5603   1.0000
   6.000   1.4258   0.01938   0.01208  -0.1899   0.5032   1.0000
   6.250   1.4396   0.02031   0.01278  -0.1870   0.4439   1.0000
   6.500   1.4428   0.02184   0.01375  -0.1824   0.3564   1.0000
   6.750   1.4395   0.02386   0.01500  -0.1771   0.2560   1.0000
   7.000   1.4419   0.02582   0.01637  -0.1732   0.1738   1.0000
   7.250   1.4457   0.02789   0.01789  -0.1697   0.1003   1.0000
   7.500   1.4489   0.03019   0.01968  -0.1661   0.0403   1.0000
   7.750   1.4555   0.03222   0.02174  -0.1627   0.0218   1.0000
   8.000   1.4650   0.03394   0.02366  -0.1597   0.0172   1.0000
   8.250   1.4715   0.03597   0.02587  -0.1564   0.0150   1.0000
   8.500   1.4772   0.03804   0.02819  -0.1531   0.0139   1.0000
   8.750   1.4829   0.04012   0.03054  -0.1500   0.0132   1.0000
   9.000   1.4885   0.04228   0.03294  -0.1470   0.0124   1.0000
   9.250   1.4950   0.04440   0.03526  -0.1444   0.0111   1.0000
   9.500   1.5007   0.04663   0.03766  -0.1419   0.0100   1.0000
   9.750   1.5029   0.04950   0.04070  -0.1393   0.0092   1.0000
  10.000   1.5073   0.05253   0.04393  -0.1368   0.0088   1.0000
  10.250   1.5149   0.05551   0.04718  -0.1346   0.0087   1.0000
  10.500   1.5229   0.05869   0.05066  -0.1326   0.0086   1.0000
  10.750   1.5294   0.06222   0.05453  -0.1305   0.0084   1.0000
  11.000   1.5325   0.06601   0.05877  -0.1284   0.0084   1.0000
  11.250   1.5314   0.07008   0.06322  -0.1263   0.0084   1.0000
  11.500   1.5264   0.07445   0.06796  -0.1244   0.0083   1.0000
  11.750   1.5181   0.07910   0.07296  -0.1227   0.0084   1.0000
  12.000   1.5064   0.08418   0.07840  -0.1215   0.0083   1.0000
  12.250   1.4933   0.08947   0.08402  -0.1209   0.0084   1.0000
  12.500   1.4787   0.09507   0.08993  -0.1210   0.0084   1.0000
  12.750   1.4630   0.10105   0.09620  -0.1219   0.0084   1.0000
  13.000   1.4463   0.10753   0.10297  -0.1237   0.0084   1.0000
  13.250   1.4301   0.11439   0.11008  -0.1265   0.0084   1.0000
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