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E61 (5.64%) (e61-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E61 (5.64%) (e61-il)
Reynolds number: 1,000,000
Max Cl/Cd: 176.6 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e61-il-1000000-n5.txt
Download as CSV file: xf-e61-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1650   0.11801   0.11618  -0.0775   0.9815   0.0046
 -10.250  -0.1583   0.11527   0.11344  -0.0781   0.9789   0.0046
 -10.000  -0.1479   0.11214   0.11031  -0.0801   0.9774   0.0047
  -9.750  -0.1367   0.10907   0.10723  -0.0821   0.9763   0.0047
  -9.500  -0.1248   0.10590   0.10406  -0.0844   0.9752   0.0047
  -8.500  -0.0002   0.07559   0.07387  -0.0974   0.9623   0.0041
  -8.250   0.0097   0.07180   0.07008  -0.0995   0.9612   0.0034
  -8.000   0.0205   0.06799   0.06628  -0.1018   0.9603   0.0031
  -7.500  -0.0364   0.08135   0.07955  -0.1003   0.9615   0.0030
  -7.000   0.0352   0.05568   0.05401  -0.1027   0.9411   0.0027
  -6.750   0.0419   0.05278   0.05111  -0.1036   0.9367   0.0028
  -6.500   0.0452   0.05020   0.04854  -0.1036   0.9299   0.0029
  -6.250   0.0585   0.04662   0.04496  -0.1067   0.9250   0.0029
  -6.000   0.0799   0.04289   0.04122  -0.1118   0.9225   0.0036
  -5.750   0.0973   0.03901   0.03732  -0.1164   0.9158   0.0039
  -5.500   0.1257   0.03400   0.03228  -0.1248   0.9116   0.0042
  -5.250   0.1648   0.02726   0.02548  -0.1381   0.9075   0.0050
  -4.750   0.2017   0.03936   0.03743  -0.1568   0.9113   0.0052
  -4.500   0.2529   0.03538   0.03337  -0.1675   0.9093   0.0055
  -4.250   0.3006   0.03141   0.02928  -0.1767   0.9043   0.0062
  -4.000   0.3717   0.02432   0.02193  -0.1922   0.9019   0.0074
  -3.750   0.4520   0.01528   0.01227  -0.2079   0.9017   0.0085
  -3.500   0.5027   0.01283   0.00940  -0.2140   0.8991   0.0090
  -3.250   0.5535   0.01024   0.00634  -0.2205   0.8964   0.0106
  -3.000   0.5883   0.00966   0.00562  -0.2224   0.8893   0.0113
  -2.750   0.6253   0.00900   0.00477  -0.2247   0.8824   0.0119
  -2.500   0.6579   0.00844   0.00404  -0.2259   0.8733   0.0124
  -2.250   0.6896   0.00805   0.00352  -0.2269   0.8639   0.0131
  -2.000   0.7212   0.00753   0.00286  -0.2278   0.8537   0.0128
  -1.750   0.7513   0.00717   0.00235  -0.2283   0.8419   0.0125
  -1.500   0.7802   0.00692   0.00198  -0.2286   0.8290   0.0122
  -1.250   0.8083   0.00676   0.00170  -0.2287   0.8156   0.0120
  -0.750   0.8629   0.00661   0.00134  -0.2284   0.7896   0.0119
  -0.500   0.8895   0.00660   0.00123  -0.2282   0.7766   0.0121
  -0.250   0.9157   0.00662   0.00116  -0.2278   0.7633   0.0127
   0.000   0.9417   0.00667   0.00113  -0.2274   0.7500   0.0148
   0.250   0.9672   0.00675   0.00115  -0.2269   0.7366   0.0162
   0.500   0.9926   0.00684   0.00117  -0.2264   0.7225   0.0207
   0.750   1.0189   0.00683   0.00128  -0.2261   0.7075   0.0932
   1.000   1.0469   0.00670   0.00145  -0.2265   0.6922   0.2753
   1.250   1.0743   0.00661   0.00164  -0.2267   0.6759   0.4455
   1.500   1.1015   0.00654   0.00186  -0.2269   0.6562   0.6342
   2.000   1.1426   0.00647   0.00219  -0.2237   0.6091   1.0000
   2.250   1.1659   0.00676   0.00234  -0.2228   0.5802   1.0000
   2.500   1.1885   0.00711   0.00253  -0.2218   0.5450   1.0000
   2.750   1.2102   0.00756   0.00276  -0.2206   0.5021   1.0000
   3.000   1.2316   0.00807   0.00303  -0.2194   0.4544   1.0000
   3.250   1.2532   0.00858   0.00335  -0.2182   0.4094   1.0000
   3.500   1.2730   0.00926   0.00371  -0.2168   0.3496   1.0000
   3.750   1.2886   0.01036   0.00427  -0.2147   0.2515   1.0000
   4.000   1.3074   0.01116   0.00474  -0.2131   0.1885   1.0000
   4.250   1.3260   0.01199   0.00523  -0.2115   0.1292   1.0000
   4.500   1.3443   0.01285   0.00578  -0.2098   0.0743   1.0000
   4.750   1.3614   0.01385   0.00646  -0.2079   0.0201   1.0000
   5.000   1.3825   0.01442   0.00697  -0.2067   0.0047   1.0000
   5.250   1.4054   0.01477   0.00735  -0.2058   0.0035   1.0000
   5.500   1.4278   0.01514   0.00776  -0.2048   0.0031   1.0000
   5.750   1.4497   0.01557   0.00823  -0.2037   0.0026   1.0000
   6.000   1.4707   0.01608   0.00880  -0.2024   0.0021   1.0000
   6.250   1.4887   0.01687   0.00973  -0.2004   0.0017   1.0000
   6.500   1.5078   0.01744   0.01035  -0.1987   0.0016   1.0000
   6.750   1.5257   0.01808   0.01106  -0.1968   0.0016   1.0000
   7.000   1.5425   0.01880   0.01190  -0.1947   0.0015   1.0000
   7.250   1.5581   0.01964   0.01283  -0.1924   0.0015   1.0000
   7.500   1.5726   0.02058   0.01387  -0.1899   0.0015   1.0000
   7.750   1.5858   0.02163   0.01503  -0.1872   0.0014   1.0000
   8.000   1.5977   0.02279   0.01630  -0.1843   0.0014   1.0000
   8.250   1.6087   0.02409   0.01772  -0.1814   0.0014   1.0000
   8.500   1.6189   0.02551   0.01927  -0.1783   0.0014   1.0000
   8.750   1.6284   0.02707   0.02097  -0.1752   0.0014   1.0000
   9.000   1.6393   0.02855   0.02257  -0.1725   0.0014   1.0000
   9.250   1.6503   0.02998   0.02413  -0.1699   0.0013   1.0000
   9.500   1.6616   0.03136   0.02565  -0.1674   0.0012   1.0000
   9.750   1.6717   0.03293   0.02734  -0.1648   0.0012   1.0000
  10.000   1.6810   0.03458   0.02913  -0.1622   0.0011   1.0000
  10.250   1.6880   0.03669   0.03142  -0.1593   0.0011   1.0000
  10.500   1.6947   0.03870   0.03358  -0.1566   0.0010   1.0000
  10.750   1.6987   0.04117   0.03625  -0.1536   0.0010   1.0000
  11.000   1.7008   0.04388   0.03916  -0.1506   0.0010   1.0000
  11.250   1.7017   0.04660   0.04208  -0.1476   0.0010   1.0000
  11.500   1.7016   0.04934   0.04500  -0.1449   0.0010   1.0000
  11.750   1.6980   0.05262   0.04849  -0.1420   0.0010   1.0000
  12.000   1.6923   0.05619   0.05227  -0.1394   0.0009   1.0000
  12.250   1.6882   0.05945   0.05569  -0.1372   0.0009   1.0000
  12.500   1.6746   0.06441   0.06091  -0.1349   0.0009   1.0000
  12.750   1.6653   0.06868   0.06536  -0.1334   0.0009   1.0000
  13.000   1.6580   0.07271   0.06957  -0.1325   0.0008   1.0000
  13.250   1.6367   0.07956   0.07669  -0.1318   0.0009   1.0000
  13.500   1.6202   0.08585   0.08319  -0.1322   0.0009   1.0000
  13.750   1.6215   0.08893   0.08631  -0.1328   0.0008   1.0000
  14.000   1.5931   0.09832   0.09599  -0.1349   0.0008   1.0000
  14.250   1.5709   0.10704   0.10493  -0.1381   0.0009   1.0000
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