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WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il)
Reynolds number: 200,000
Max Cl/Cd: 85.17 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63137-il-200000-n5.txt
Download as CSV file: xf-fx63137-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2513   0.06200   0.05840  -0.1032   0.9344   0.0184
  -9.500  -0.3218   0.03337   0.02864  -0.1426   0.9066   0.0181
  -9.250  -0.2866   0.03087   0.02595  -0.1500   0.9007   0.0189
  -9.000  -0.2465   0.02887   0.02372  -0.1566   0.8968   0.0202
  -8.750  -0.2162   0.02648   0.02091  -0.1614   0.8885   0.0220
  -8.500  -0.1777   0.02628   0.02072  -0.1646   0.8835   0.0233
  -8.250  -0.1405   0.02431   0.01829  -0.1692   0.8779   0.0251
  -8.000  -0.1092   0.02340   0.01725  -0.1712   0.8702   0.0258
  -7.750  -0.0731   0.02246   0.01614  -0.1740   0.8647   0.0265
  -7.500  -0.0423   0.02153   0.01502  -0.1757   0.8580   0.0272
  -7.250  -0.0102   0.02058   0.01385  -0.1774   0.8516   0.0281
  -7.000   0.0248   0.01964   0.01261  -0.1795   0.8466   0.0293
  -6.750   0.0531   0.01915   0.01208  -0.1802   0.8399   0.0301
  -6.500   0.0845   0.01861   0.01142  -0.1814   0.8342   0.0310
  -6.250   0.1176   0.01806   0.01071  -0.1828   0.8290   0.0324
  -6.000   0.1454   0.01757   0.01006  -0.1831   0.8214   0.0337
  -5.750   0.1766   0.01705   0.00950  -0.1842   0.8150   0.0349
  -5.500   0.2063   0.01658   0.00896  -0.1848   0.8087   0.0359
  -5.250   0.2360   0.01612   0.00843  -0.1855   0.8025   0.0369
  -5.000   0.2680   0.01567   0.00789  -0.1865   0.7975   0.0380
  -4.750   0.2983   0.01529   0.00741  -0.1873   0.7919   0.0390
  -4.500   0.3298   0.01481   0.00692  -0.1884   0.7858   0.0402
  -4.250   0.3631   0.01443   0.00647  -0.1898   0.7804   0.0420
  -4.000   0.3941   0.01412   0.00609  -0.1907   0.7743   0.0446
  -3.750   0.4258   0.01382   0.00577  -0.1917   0.7682   0.0485
  -3.500   0.4585   0.01359   0.00549  -0.1929   0.7631   0.0553
  -3.250   0.4885   0.01341   0.00529  -0.1934   0.7568   0.0662
  -3.000   0.5205   0.01315   0.00508  -0.1945   0.7508   0.0850
  -2.750   0.5532   0.01294   0.00488  -0.1957   0.7455   0.1166
  -2.500   0.5853   0.01260   0.00476  -0.1970   0.7386   0.1879
  -2.250   0.6201   0.01219   0.00469  -0.1990   0.7325   0.3088
  -2.000   0.6513   0.01208   0.00474  -0.1998   0.7265   0.3810
  -1.750   0.6804   0.01209   0.00482  -0.2000   0.7198   0.4231
  -1.500   0.7099   0.01215   0.00488  -0.2002   0.7142   0.4569
  -1.250   0.7381   0.01224   0.00499  -0.2002   0.7078   0.4826
  -1.000   0.7663   0.01232   0.00506  -0.2001   0.7007   0.5017
  -0.750   0.7947   0.01240   0.00510  -0.2000   0.6943   0.5156
  -0.500   0.8222   0.01249   0.00517  -0.1998   0.6864   0.5300
  -0.250   0.8506   0.01258   0.00520  -0.1998   0.6795   0.5451
   0.000   0.8777   0.01268   0.00530  -0.1995   0.6713   0.5581
   0.250   0.9055   0.01277   0.00534  -0.1993   0.6642   0.5673
   0.500   0.9328   0.01286   0.00541  -0.1992   0.6557   0.5758
   0.750   0.9600   0.01294   0.00547  -0.1989   0.6472   0.5823
   1.000   0.9865   0.01303   0.00556  -0.1986   0.6373   0.5897
   1.250   1.0136   0.01313   0.00561  -0.1983   0.6279   0.5969
   1.500   1.0400   0.01323   0.00571  -0.1979   0.6180   0.6037
   1.750   1.0670   0.01336   0.00579  -0.1977   0.6088   0.6117
   2.000   1.0933   0.01349   0.00592  -0.1973   0.5995   0.6182
   2.250   1.1197   0.01363   0.00605  -0.1970   0.5900   0.6263
   2.500   1.1457   0.01379   0.00620  -0.1966   0.5797   0.6333
   2.750   1.1710   0.01394   0.00635  -0.1961   0.5667   0.6401
   3.000   1.1959   0.01414   0.00648  -0.1955   0.5522   0.6474
   3.250   1.2196   0.01436   0.00667  -0.1946   0.5365   0.6536
   3.500   1.2432   0.01461   0.00687  -0.1938   0.5194   0.6612
   3.750   1.2665   0.01487   0.00710  -0.1929   0.5019   0.6686
   4.000   1.2894   0.01517   0.00735  -0.1920   0.4860   0.6772
   4.250   1.3122   0.01548   0.00763  -0.1911   0.4719   0.6857
   4.500   1.3351   0.01579   0.00793  -0.1902   0.4586   0.6952
   4.750   1.3576   0.01610   0.00826  -0.1893   0.4443   0.7046
   5.250   1.4008   0.01681   0.00896  -0.1871   0.4183   0.7259
   5.500   1.4216   0.01720   0.00936  -0.1859   0.4063   0.7369
   5.750   1.4416   0.01761   0.00977  -0.1846   0.3935   0.7493
   6.000   1.4608   0.01801   0.01020  -0.1831   0.3785   0.7625
   6.250   1.4779   0.01847   0.01067  -0.1812   0.3630   0.7775
   6.500   1.4917   0.01901   0.01119  -0.1788   0.3494   0.7947
   6.750   1.5049   0.01953   0.01172  -0.1763   0.3343   0.8149
   7.000   1.5169   0.02000   0.01225  -0.1735   0.3166   0.8422
   7.500   1.5272   0.02128   0.01350  -0.1658   0.2844   1.0000
   7.750   1.5403   0.02213   0.01430  -0.1638   0.2662   1.0000
   8.000   1.5518   0.02307   0.01520  -0.1617   0.2462   1.0000
   8.250   1.5607   0.02420   0.01625  -0.1592   0.2322   1.0000
   8.500   1.5709   0.02530   0.01733  -0.1571   0.2207   1.0000
   8.750   1.5825   0.02636   0.01841  -0.1552   0.2055   1.0000
   9.000   1.5902   0.02771   0.01972  -0.1530   0.1887   1.0000
   9.250   1.5964   0.02923   0.02118  -0.1508   0.1767   1.0000
   9.500   1.6032   0.03078   0.02272  -0.1487   0.1660   1.0000
   9.750   1.6131   0.03214   0.02413  -0.1471   0.1492   1.0000
  10.000   1.6167   0.03407   0.02600  -0.1450   0.1360   1.0000
  10.250   1.6203   0.03609   0.02798  -0.1432   0.1275   1.0000
  10.500   1.6286   0.03775   0.02973  -0.1417   0.1176   1.0000
  10.750   1.6345   0.03969   0.03170  -0.1402   0.1056   1.0000
  11.000   1.6370   0.04201   0.03401  -0.1387   0.0977   1.0000
  11.250   1.6391   0.04446   0.03645  -0.1373   0.0926   1.0000
  11.500   1.6431   0.04677   0.03883  -0.1360   0.0880   1.0000
  11.750   1.6464   0.04924   0.04138  -0.1349   0.0835   1.0000
  12.000   1.6467   0.05211   0.04430  -0.1339   0.0797   1.0000
  12.250   1.6538   0.05428   0.04660  -0.1331   0.0759   1.0000
  12.500   1.6585   0.05680   0.04920  -0.1324   0.0716   1.0000
  12.750   1.6608   0.05965   0.05211  -0.1318   0.0683   1.0000
  13.000   1.6638   0.06250   0.05504  -0.1312   0.0659   1.0000
  13.250   1.6653   0.06559   0.05818  -0.1309   0.0634   1.0000
  13.500   1.6653   0.06897   0.06162  -0.1306   0.0613   1.0000
  13.750   1.6649   0.07251   0.06522  -0.1305   0.0592   1.0000
  14.000   1.6668   0.07578   0.06862  -0.1304   0.0578   1.0000
  14.250   1.6678   0.07924   0.07220  -0.1305   0.0563   1.0000
  14.500   1.6676   0.08293   0.07599  -0.1307   0.0548   1.0000
  14.750   1.6660   0.08690   0.08007  -0.1311   0.0534   1.0000
  15.000   1.6628   0.09119   0.08444  -0.1317   0.0519   1.0000
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