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WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il)
Reynolds number: 500,000
Max Cl/Cd: 119.12 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63137-il-500000.txt
Download as CSV file: xf-fx63137-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.4234   0.06143   0.05891  -0.0974   0.9842   0.0123
 -11.250  -0.4620   0.04389   0.04101  -0.1184   0.9723   0.0121
 -11.000  -0.4661   0.03660   0.03349  -0.1288   0.9595   0.0120
 -10.750  -0.4562   0.02923   0.02569  -0.1419   0.9466   0.0123
 -10.500  -0.4212   0.02627   0.02257  -0.1503   0.9407   0.0126
 -10.250  -0.3842   0.02447   0.02064  -0.1563   0.9342   0.0130
 -10.000  -0.3415   0.02259   0.01855  -0.1628   0.9309   0.0137
  -9.750  -0.2987   0.02052   0.01604  -0.1691   0.9261   0.0151
  -9.500  -0.2591   0.01942   0.01492  -0.1733   0.9197   0.0161
  -9.250  -0.2148   0.01840   0.01368  -0.1782   0.9147   0.0176
  -9.000  -0.1784   0.01729   0.01238  -0.1814   0.9064   0.0189
  -8.750  -0.1400   0.01671   0.01172  -0.1844   0.8989   0.0203
  -8.500  -0.1066   0.01615   0.01098  -0.1863   0.8901   0.0213
  -8.250  -0.0727   0.01536   0.01005  -0.1884   0.8820   0.0223
  -8.000  -0.0428   0.01508   0.00973  -0.1893   0.8733   0.0233
  -7.750  -0.0113   0.01476   0.00929  -0.1904   0.8653   0.0243
  -7.500   0.0176   0.01436   0.00876  -0.1910   0.8572   0.0250
  -7.250   0.0476   0.01388   0.00816  -0.1918   0.8493   0.0255
  -7.000   0.0766   0.01354   0.00777  -0.1924   0.8417   0.0262
  -6.750   0.1058   0.01342   0.00760  -0.1928   0.8344   0.0272
  -6.500   0.1362   0.01326   0.00734  -0.1935   0.8284   0.0283
  -6.250   0.1644   0.01301   0.00701  -0.1937   0.8219   0.0291
  -6.000   0.1943   0.01264   0.00658  -0.1944   0.8159   0.0299
  -5.750   0.2238   0.01247   0.00639  -0.1949   0.8100   0.0310
  -5.500   0.2526   0.01220   0.00607  -0.1953   0.8034   0.0318
  -5.250   0.2832   0.01191   0.00569  -0.1960   0.7974   0.0324
  -5.000   0.3128   0.01163   0.00537  -0.1964   0.7913   0.0330
  -4.750   0.3428   0.01138   0.00505  -0.1970   0.7853   0.0336
  -4.500   0.3747   0.01108   0.00470  -0.1980   0.7800   0.0347
  -4.250   0.4042   0.01086   0.00448  -0.1985   0.7738   0.0364
  -4.000   0.4342   0.01067   0.00424  -0.1990   0.7672   0.0381
  -3.750   0.4657   0.01046   0.00395  -0.1998   0.7613   0.0396
  -3.500   0.4968   0.01013   0.00362  -0.2007   0.7545   0.0423
  -3.250   0.5282   0.00991   0.00334  -0.2015   0.7481   0.0484
  -3.000   0.5588   0.00972   0.00320  -0.2021   0.7413   0.0637
  -2.750   0.5899   0.00949   0.00303  -0.2029   0.7341   0.0913
  -2.500   0.6220   0.00923   0.00289  -0.2040   0.7271   0.1564
  -2.250   0.6545   0.00887   0.00278  -0.2053   0.7190   0.2516
  -2.000   0.6861   0.00869   0.00273  -0.2063   0.7119   0.3255
  -1.750   0.7160   0.00858   0.00274  -0.2068   0.7041   0.3771
  -1.500   0.7454   0.00856   0.00276  -0.2071   0.6975   0.4144
  -1.250   0.7746   0.00856   0.00280  -0.2073   0.6911   0.4429
  -1.000   0.8032   0.00859   0.00284  -0.2073   0.6845   0.4622
  -0.750   0.8317   0.00866   0.00287  -0.2074   0.6782   0.4792
  -0.500   0.8601   0.00871   0.00295  -0.2074   0.6713   0.4983
  -0.250   0.8882   0.00881   0.00302  -0.2073   0.6648   0.5163
   0.000   0.9163   0.00889   0.00311  -0.2073   0.6581   0.5313
   0.250   0.9443   0.00898   0.00317  -0.2072   0.6506   0.5425
   0.500   0.9721   0.00906   0.00325  -0.2071   0.6436   0.5518
   0.750   0.9998   0.00913   0.00331  -0.2070   0.6350   0.5614
   1.000   1.0268   0.00922   0.00338  -0.2067   0.6249   0.5699
   1.250   1.0530   0.00936   0.00344  -0.2063   0.6127   0.5787
   1.500   1.0792   0.00948   0.00355  -0.2058   0.5994   0.5881
   1.750   1.1056   0.00961   0.00366  -0.2055   0.5863   0.5983
   2.000   1.1319   0.00975   0.00378  -0.2051   0.5739   0.6084
   2.250   1.1579   0.00990   0.00390  -0.2047   0.5616   0.6168
   2.500   1.1840   0.01007   0.00404  -0.2043   0.5501   0.6249
   2.750   1.2100   0.01024   0.00417  -0.2039   0.5387   0.6318
   3.000   1.2354   0.01043   0.00434  -0.2034   0.5268   0.6386
   3.250   1.2611   0.01063   0.00451  -0.2030   0.5134   0.6466
   3.500   1.2865   0.01080   0.00468  -0.2025   0.4991   0.6537
   3.750   1.3110   0.01105   0.00488  -0.2019   0.4848   0.6612
   4.000   1.3354   0.01131   0.00510  -0.2013   0.4707   0.6682
   4.250   1.3596   0.01157   0.00533  -0.2006   0.4557   0.6760
   4.500   1.3836   0.01185   0.00557  -0.2000   0.4383   0.6840
   4.750   1.4065   0.01216   0.00584  -0.1991   0.4223   0.6923
   5.000   1.4295   0.01249   0.00613  -0.1983   0.4094   0.7013
   5.250   1.4520   0.01283   0.00646  -0.1973   0.3965   0.7109
   5.500   1.4754   0.01312   0.00675  -0.1966   0.3812   0.7213
   5.750   1.4970   0.01349   0.00709  -0.1955   0.3637   0.7337
   6.000   1.5169   0.01394   0.00749  -0.1942   0.3483   0.7467
   6.250   1.5369   0.01438   0.00791  -0.1928   0.3322   0.7606
   6.500   1.5570   0.01478   0.00831  -0.1915   0.3105   0.7757
   6.750   1.5717   0.01539   0.00883  -0.1893   0.2890   0.7927
   7.000   1.5875   0.01589   0.00933  -0.1872   0.2729   0.8136
   7.250   1.6009   0.01646   0.00989  -0.1847   0.2498   0.8411
   7.500   1.6066   0.01700   0.01045  -0.1807   0.2330   0.9042
   7.750   1.6153   0.01758   0.01100  -0.1774   0.2211   1.0000
   8.000   1.6295   0.01832   0.01169  -0.1753   0.2009   1.0000
   8.500   1.6485   0.02037   0.01353  -0.1700   0.1670   1.0000
   9.000   1.6622   0.02290   0.01583  -0.1645   0.1267   1.0000
   9.250   1.6712   0.02408   0.01699  -0.1621   0.1083   1.0000
   9.500   1.6754   0.02566   0.01845  -0.1594   0.0947   1.0000
   9.750   1.6840   0.02699   0.01978  -0.1573   0.0876   1.0000
  10.000   1.6913   0.02846   0.02126  -0.1552   0.0818   1.0000
  10.250   1.7017   0.02974   0.02259  -0.1535   0.0771   1.0000
  10.500   1.7118   0.03108   0.02396  -0.1519   0.0711   1.0000
  10.750   1.7191   0.03270   0.02557  -0.1501   0.0672   1.0000
  11.000   1.7269   0.03434   0.02723  -0.1485   0.0648   1.0000
  11.250   1.7335   0.03614   0.02905  -0.1470   0.0624   1.0000
  11.500   1.7391   0.03809   0.03103  -0.1454   0.0602   1.0000
  11.750   1.7464   0.03992   0.03295  -0.1441   0.0588   1.0000
  12.000   1.7530   0.04188   0.03500  -0.1429   0.0574   1.0000
  12.250   1.7573   0.04414   0.03732  -0.1416   0.0556   1.0000
  12.500   1.7602   0.04661   0.03985  -0.1404   0.0540   1.0000
  12.750   1.7619   0.04930   0.04261  -0.1393   0.0525   1.0000
  13.000   1.7613   0.05236   0.04575  -0.1382   0.0510   1.0000
  13.250   1.7684   0.05455   0.04804  -0.1376   0.0499   1.0000
  13.500   1.7775   0.05655   0.05013  -0.1371   0.0488   1.0000
  13.750   1.7862   0.05862   0.05228  -0.1366   0.0466   1.0000
  14.000   1.7907   0.06128   0.05500  -0.1361   0.0446   1.0000
  14.250   1.7917   0.06446   0.05825  -0.1357   0.0430   1.0000
  14.500   1.7975   0.06707   0.06092  -0.1355   0.0411   1.0000
  14.750   1.8097   0.06880   0.06271  -0.1353   0.0382   1.0000
  15.000   1.8142   0.07163   0.06558  -0.1352   0.0352   1.0000
  15.250   1.8189   0.07450   0.06847  -0.1351   0.0299   1.0000
  15.500   1.8116   0.07917   0.07303  -0.1354   0.0203   1.0000
  15.750   1.7945   0.08550   0.07936  -0.1360   0.0102   1.0000
  16.000   1.7802   0.09160   0.08553  -0.1368   0.0069   1.0000
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