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WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il)
Reynolds number: 200,000
Max Cl/Cd: 90.58 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63137-il-200000.txt
Download as CSV file: xf-fx63137-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 63-137 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2059   0.12152   0.11814  -0.0557   0.9866   0.0431
 -10.250  -0.1992   0.11617   0.11279  -0.0643   0.9835   0.0448
 -10.000  -0.1931   0.11079   0.10744  -0.0702   0.9770   0.0452
  -9.750  -0.1662   0.10774   0.10436  -0.0702   0.9747   0.0461
  -9.500  -0.1450   0.10407   0.10069  -0.0738   0.9723   0.0478
  -9.250  -0.1335   0.10011   0.09673  -0.0775   0.9655   0.0496
  -9.000  -0.1372   0.09181   0.08845  -0.0918   0.9592   0.0517
  -8.750  -0.1033   0.09038   0.08701  -0.0885   0.9585   0.0536
  -8.500  -0.0925   0.08726   0.08389  -0.0911   0.9500   0.0572
  -8.250  -0.0870   0.07999   0.07665  -0.1011   0.9452   0.0602
  -8.000  -0.0651   0.07860   0.07524  -0.1010   0.9398   0.0658
  -7.500  -0.0944   0.03637   0.03158  -0.1615   0.9131   0.0450
  -7.250  -0.0802   0.03975   0.03565  -0.1538   0.9057   0.0490
  -7.000  -0.0366   0.03204   0.02689  -0.1675   0.9015   0.0509
  -6.750   0.0088   0.02842   0.02273  -0.1739   0.8993   0.0510
  -6.500   0.0569   0.02565   0.01943  -0.1799   0.8974   0.0521
  -6.250   0.0826   0.02455   0.01838  -0.1802   0.8900   0.0536
  -6.000   0.1206   0.02328   0.01694  -0.1829   0.8855   0.0554
  -5.750   0.1638   0.02189   0.01525  -0.1864   0.8822   0.0573
  -5.500   0.2016   0.02067   0.01376  -0.1887   0.8780   0.0580
  -5.250   0.2287   0.01978   0.01272  -0.1887   0.8709   0.0581
  -5.000   0.2655   0.01879   0.01156  -0.1904   0.8665   0.0585
  -4.750   0.3024   0.01789   0.01055  -0.1922   0.8622   0.0597
  -4.500   0.3266   0.01726   0.00998  -0.1916   0.8544   0.0612
  -4.250   0.3616   0.01658   0.00930  -0.1930   0.8493   0.0632
  -4.000   0.3947   0.01605   0.00872  -0.1941   0.8439   0.0658
  -3.750   0.4251   0.01549   0.00818  -0.1948   0.8369   0.0699
  -3.500   0.4648   0.01478   0.00750  -0.1975   0.8319   0.0811
  -3.250   0.5012   0.01421   0.00700  -0.1997   0.8262   0.1132
  -3.000   0.5436   0.01307   0.00676  -0.2042   0.8198   0.3471
  -2.750   0.5779   0.01301   0.00674  -0.2053   0.8143   0.4194
  -2.500   0.6055   0.01314   0.00687  -0.2050   0.8071   0.4552
  -2.250   0.6350   0.01326   0.00697  -0.2050   0.8003   0.4871
  -2.000   0.6658   0.01342   0.00705  -0.2052   0.7948   0.5104
  -1.750   0.6910   0.01362   0.00726  -0.2045   0.7874   0.5289
  -1.500   0.7206   0.01377   0.00736  -0.2044   0.7816   0.5480
  -1.250   0.7471   0.01397   0.00755  -0.2038   0.7749   0.5647
  -1.000   0.7745   0.01410   0.00765  -0.2034   0.7678   0.5792
  -0.750   0.8048   0.01419   0.00767  -0.2035   0.7623   0.5920
  -0.500   0.8278   0.01431   0.00785  -0.2023   0.7536   0.6034
  -0.250   0.8577   0.01435   0.00782  -0.2023   0.7472   0.6167
   0.000   0.8835   0.01450   0.00796  -0.2018   0.7393   0.6299
   0.250   0.9104   0.01451   0.00798  -0.2012   0.7324   0.6390
   0.500   0.9389   0.01456   0.00798  -0.2012   0.7248   0.6484
   0.750   0.9654   0.01456   0.00798  -0.2007   0.7167   0.6556
   1.000   0.9945   0.01460   0.00795  -0.2008   0.7087   0.6650
   1.250   1.0203   0.01458   0.00796  -0.2002   0.7000   0.6718
   1.500   1.0487   0.01462   0.00795  -0.2002   0.6918   0.6811
   1.750   1.0749   0.01462   0.00797  -0.1997   0.6835   0.6882
   2.000   1.1031   0.01468   0.00800  -0.1997   0.6755   0.6978
   2.250   1.1289   0.01470   0.00804  -0.1991   0.6669   0.7054
   2.500   1.1565   0.01479   0.00811  -0.1990   0.6581   0.7151
   2.750   1.1820   0.01479   0.00811  -0.1983   0.6482   0.7229
   3.000   1.2074   0.01484   0.00817  -0.1978   0.6362   0.7326
   3.250   1.2319   0.01484   0.00818  -0.1969   0.6243   0.7403
   3.500   1.2591   0.01488   0.00814  -0.1966   0.6126   0.7503
   3.750   1.2818   0.01495   0.00826  -0.1955   0.5999   0.7587
   4.000   1.3065   0.01508   0.00841  -0.1949   0.5877   0.7692
   4.250   1.3308   0.01521   0.00854  -0.1941   0.5760   0.7802
   4.500   1.3545   0.01534   0.00868  -0.1932   0.5642   0.7915
   4.750   1.3781   0.01550   0.00890  -0.1924   0.5525   0.8044
   5.000   1.4017   0.01569   0.00909  -0.1915   0.5416   0.8189
   5.250   1.4244   0.01589   0.00929  -0.1905   0.5303   0.8350
   5.500   1.4444   0.01607   0.00956  -0.1890   0.5176   0.8529
   5.750   1.4626   0.01622   0.00977  -0.1871   0.5052   0.8752
   6.000   1.4751   0.01629   0.00988  -0.1839   0.4938   0.9166
   6.250   1.4964   0.01652   0.01010  -0.1829   0.4812   1.0000
   6.500   1.5214   0.01696   0.01050  -0.1827   0.4665   1.0000
   6.750   1.5438   0.01740   0.01092  -0.1821   0.4513   1.0000
   7.000   1.5645   0.01786   0.01136  -0.1810   0.4362   1.0000
   7.250   1.5829   0.01838   0.01183  -0.1795   0.4206   1.0000
   7.500   1.6001   0.01895   0.01235  -0.1778   0.4064   1.0000
   7.750   1.6154   0.01952   0.01291  -0.1758   0.3926   1.0000
   8.000   1.6292   0.02012   0.01353  -0.1735   0.3775   1.0000
   8.250   1.6412   0.02080   0.01419  -0.1710   0.3623   1.0000
   8.500   1.6511   0.02162   0.01495  -0.1682   0.3480   1.0000
   8.750   1.6605   0.02250   0.01581  -0.1655   0.3323   1.0000
   9.000   1.6707   0.02336   0.01673  -0.1630   0.3138   1.0000
   9.250   1.6765   0.02449   0.01781  -0.1600   0.2956   1.0000
   9.500   1.6813   0.02579   0.01907  -0.1570   0.2789   1.0000
   9.750   1.6865   0.02715   0.02043  -0.1543   0.2582   1.0000
  10.000   1.6862   0.02895   0.02213  -0.1512   0.2384   1.0000
  10.250   1.6856   0.03093   0.02405  -0.1483   0.2207   1.0000
  10.500   1.6859   0.03299   0.02608  -0.1458   0.1959   1.0000
  10.750   1.6802   0.03567   0.02863  -0.1430   0.1770   1.0000
  11.000   1.6763   0.03840   0.03131  -0.1406   0.1551   1.0000
  11.250   1.6700   0.04149   0.03429  -0.1384   0.1382   1.0000
  11.500   1.6620   0.04490   0.03761  -0.1364   0.1277   1.0000
  11.750   1.6618   0.04769   0.04047  -0.1349   0.1179   1.0000
  12.000   1.6608   0.05065   0.04345  -0.1336   0.1113   1.0000
  12.250   1.6633   0.05332   0.04617  -0.1326   0.1056   1.0000
  12.500   1.6624   0.05645   0.04929  -0.1316   0.1015   1.0000
  12.750   1.6654   0.05920   0.05214  -0.1309   0.0976   1.0000
  13.000   1.6658   0.06233   0.05528  -0.1302   0.0943   1.0000
  13.250   1.6632   0.06586   0.05878  -0.1295   0.0909   1.0000
  13.500   1.6685   0.06854   0.06160  -0.1291   0.0880   1.0000
  13.750   1.6720   0.07147   0.06464  -0.1289   0.0849   1.0000
  14.000   1.6742   0.07460   0.06784  -0.1286   0.0825   1.0000
  14.250   1.6756   0.07781   0.07104  -0.1283   0.0802   1.0000
  14.500   1.6807   0.08064   0.07400  -0.1282   0.0783   1.0000
  14.750   1.6858   0.08352   0.07705  -0.1282   0.0763   1.0000
  15.000   1.6904   0.08649   0.08015  -0.1284   0.0743   1.0000
  15.250   1.6942   0.08959   0.08335  -0.1286   0.0725   1.0000
  15.500   1.6968   0.09287   0.08669  -0.1290   0.0707   1.0000
  15.750   1.6991   0.09615   0.09001  -0.1293   0.0688   1.0000
  16.000   1.7021   0.09949   0.09354  -0.1299   0.0671   1.0000
  16.250   1.7036   0.10311   0.09729  -0.1308   0.0649   1.0000
  16.500   1.7047   0.10678   0.10106  -0.1318   0.0632   1.0000
  16.750   1.7047   0.11058   0.10487  -0.1328   0.0611   1.0000
  17.000   1.7075   0.11381   0.10814  -0.1335   0.0592   1.0000
  17.250   1.7078   0.11770   0.11223  -0.1348   0.0577   1.0000
  17.500   1.7070   0.12182   0.11650  -0.1364   0.0557   1.0000
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