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FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il)
Reynolds number: 100,000
Max Cl/Cd: 60.51 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63137sm-il-100000.txt
Download as CSV file: xf-fx63137sm-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-137 13.7% smoothed                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2302   0.11133   0.10701  -0.0485   0.9751   0.1054
  -7.750  -0.2291   0.10879   0.10449  -0.0531   0.9667   0.1105
  -7.500  -0.2619   0.10841   0.10422  -0.0617   0.9535   0.1124
  -7.250  -0.2052   0.10149   0.09723  -0.0583   0.9545   0.1166
  -7.000  -0.1870   0.09840   0.09413  -0.0613   0.9495   0.1224
  -6.750  -0.2168   0.09747   0.09329  -0.0679   0.9360   0.1276
  -6.500  -0.2126   0.09367   0.08953  -0.0674   0.9280   0.1296
  -6.250  -0.1749   0.09037   0.08618  -0.0662   0.9257   0.1347
  -6.000  -0.1803   0.08835   0.08419  -0.0682   0.9155   0.1414
  -5.750  -0.1696   0.08386   0.07973  -0.0740   0.9089   0.1475
  -5.500  -0.1710   0.07979   0.07565  -0.0871   0.8957   0.1607
  -5.250  -0.1492   0.07801   0.07390  -0.0787   0.8934   0.1647
  -5.000  -0.1396   0.07637   0.07227  -0.0779   0.8857   0.1728
  -4.750  -0.0386   0.04454   0.03862  -0.1382   0.8811   0.0873
  -4.500   0.0302   0.03857   0.03170  -0.1489   0.8792   0.0772
  -4.250   0.0908   0.03515   0.02757  -0.1561   0.8770   0.0762
  -4.000   0.1450   0.03322   0.02526  -0.1611   0.8748   0.0810
  -3.750   0.1684   0.03254   0.02432  -0.1609   0.8661   0.0828
  -3.500   0.2113   0.03091   0.02262  -0.1636   0.8621   0.0875
  -3.250   0.2591   0.02969   0.02132  -0.1669   0.8592   0.0986
  -3.000   0.3044   0.02842   0.02025  -0.1699   0.8560   0.1160
  -2.750   0.3315   0.02801   0.02003  -0.1707   0.8471   0.1467
  -2.500   0.3965   0.02655   0.01992  -0.1781   0.8447   0.4690
  -2.250   0.4359   0.02684   0.02017  -0.1785   0.8415   0.5260
  -2.000   0.4425   0.02789   0.02128  -0.1745   0.8304   0.5495
  -1.750   0.4780   0.02797   0.02130  -0.1744   0.8262   0.5813
  -1.500   0.5165   0.02778   0.02108  -0.1745   0.8238   0.6044
  -1.250   0.5205   0.02875   0.02205  -0.1706   0.8115   0.6198
  -1.000   0.5564   0.02852   0.02179  -0.1704   0.8082   0.6423
  -0.750   0.5699   0.02915   0.02241  -0.1679   0.7985   0.6574
  -0.500   0.6069   0.02890   0.02208  -0.1690   0.7934   0.6728
  -0.250   0.6550   0.02828   0.02134  -0.1718   0.7907   0.6879
   0.000   0.6666   0.02897   0.02203  -0.1694   0.7801   0.6981
   0.250   0.7064   0.02853   0.02153  -0.1709   0.7756   0.7108
   0.500   0.7538   0.02780   0.02071  -0.1736   0.7728   0.7244
   0.750   0.7674   0.02860   0.02151  -0.1719   0.7615   0.7362
   1.000   0.8071   0.02799   0.02086  -0.1731   0.7575   0.7483
   1.250   0.8527   0.02721   0.02002  -0.1752   0.7545   0.7618
   1.500   0.8625   0.02810   0.02095  -0.1729   0.7424   0.7734
   1.750   0.9074   0.02733   0.02013  -0.1750   0.7388   0.7881
   2.000   0.9186   0.02806   0.02092  -0.1725   0.7277   0.8007
   2.250   0.9578   0.02738   0.02021  -0.1736   0.7230   0.8157
   2.500   0.9767   0.02771   0.02058  -0.1721   0.7139   0.8303
   2.750   1.0085   0.02732   0.02018  -0.1722   0.7073   0.8473
   3.250   1.0556   0.02711   0.02001  -0.1701   0.6915   0.8851
   3.750   1.0925   0.02665   0.01966  -0.1659   0.6755   0.9479
   4.000   1.1499   0.02572   0.01866  -0.1707   0.6705   1.0000
   4.250   1.1808   0.02637   0.01937  -0.1724   0.6589   1.0000
   4.500   1.2378   0.02563   0.01852  -0.1772   0.6533   1.0000
   4.750   1.2641   0.02627   0.01922  -0.1777   0.6413   1.0000
   5.000   1.3114   0.02584   0.01872  -0.1809   0.6342   1.0000
   5.250   1.3392   0.02620   0.01911  -0.1812   0.6229   1.0000
   5.500   1.3693   0.02644   0.01938  -0.1817   0.6126   1.0000
   5.750   1.4098   0.02610   0.01896  -0.1835   0.6037   1.0000
   6.000   1.4320   0.02657   0.01950  -0.1827   0.5916   1.0000
   6.250   1.4632   0.02650   0.01942  -0.1830   0.5802   1.0000
   6.500   1.4970   0.02602   0.01885  -0.1833   0.5665   1.0000
   6.750   1.5261   0.02570   0.01844  -0.1829   0.5512   1.0000
   7.000   1.5512   0.02565   0.01836  -0.1821   0.5360   1.0000
   7.250   1.5708   0.02596   0.01872  -0.1805   0.5215   1.0000
   7.500   1.5908   0.02630   0.01910  -0.1791   0.5071   1.0000
   7.750   1.6111   0.02663   0.01947  -0.1777   0.4927   1.0000
   8.000   1.6308   0.02698   0.01982  -0.1762   0.4779   1.0000
   8.250   1.6492   0.02737   0.02022  -0.1745   0.4628   1.0000
   8.500   1.6658   0.02783   0.02070  -0.1725   0.4473   1.0000
   8.750   1.6798   0.02837   0.02124  -0.1702   0.4313   1.0000
   9.000   1.6911   0.02900   0.02188  -0.1675   0.4149   1.0000
   9.250   1.6982   0.02971   0.02261  -0.1641   0.3985   1.0000
   9.500   1.7027   0.03057   0.02348  -0.1604   0.3818   1.0000
   9.750   1.7046   0.03160   0.02454  -0.1566   0.3642   1.0000
  10.000   1.7043   0.03284   0.02577  -0.1527   0.3457   1.0000
  10.250   1.7023   0.03430   0.02719  -0.1488   0.3264   1.0000
  10.500   1.6992   0.03601   0.02879  -0.1451   0.3064   1.0000
  10.750   1.6921   0.03817   0.03095  -0.1414   0.2849   1.0000
  11.000   1.6853   0.04058   0.03327  -0.1382   0.2637   1.0000
  11.250   1.6800   0.04315   0.03568  -0.1353   0.2441   1.0000
  11.500   1.6770   0.04579   0.03818  -0.1329   0.2263   1.0000
  11.750   1.6767   0.04838   0.04067  -0.1308   0.2110   1.0000
  12.000   1.6789   0.05085   0.04308  -0.1291   0.1983   1.0000
  12.250   1.6833   0.05326   0.04553  -0.1277   0.1875   1.0000
  12.500   1.6939   0.05530   0.04750  -0.1265   0.1786   1.0000
  12.750   1.7041   0.05733   0.04956  -0.1254   0.1710   1.0000
  13.000   1.7189   0.05918   0.05141  -0.1245   0.1643   1.0000
  13.250   1.7289   0.06129   0.05362  -0.1236   0.1583   1.0000
  13.500   1.7550   0.06250   0.05467  -0.1232   0.1523   1.0000
  13.750   1.7595   0.06513   0.05760  -0.1221   0.1484   1.0000
  14.000   1.7727   0.06718   0.05976  -0.1214   0.1442   1.0000
  14.250   1.8128   0.06788   0.06024  -0.1217   0.1389   1.0000
  14.500   1.8084   0.07112   0.06384  -0.1203   0.1365   1.0000
  14.750   1.8073   0.07434   0.06735  -0.1193   0.1339   1.0000
  15.000   1.8124   0.07720   0.07043  -0.1185   0.1312   1.0000
  15.250   1.8280   0.07928   0.07256  -0.1181   0.1282   1.0000
  15.500   1.8540   0.08141   0.07470  -0.1180   0.1249   1.0000
  15.750   1.8366   0.08594   0.07961  -0.1170   0.1237   1.0000
  16.000   1.8185   0.09085   0.08488  -0.1164   0.1225   1.0000
  16.250   1.7998   0.09611   0.09048  -0.1163   0.1213   1.0000
  16.500   1.7791   0.10188   0.09657  -0.1169   0.1202   1.0000
  16.750   1.7555   0.10828   0.10328  -0.1181   0.1193   1.0000
  17.000   1.7241   0.11611   0.11143  -0.1205   0.1188   1.0000
  17.250   1.6705   0.12793   0.12364  -0.1258   0.1191   1.0000
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