Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il)
Reynolds number: 500,000
Max Cl/Cd: 117.86 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63137sm-il-500000-n5.txt
Download as CSV file: xf-fx63137sm-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1537   0.10494   0.10243  -0.0787   0.9639   0.0110
 -10.000  -0.2865   0.03068   0.02710  -0.1546   0.9013   0.0115
  -9.750  -0.2470   0.02597   0.02196  -0.1688   0.8871   0.0117
  -9.250  -0.1883   0.02136   0.01669  -0.1792   0.8623   0.0123
  -9.000  -0.1609   0.01992   0.01497  -0.1815   0.8525   0.0126
  -8.750  -0.1335   0.01873   0.01353  -0.1831   0.8430   0.0130
  -8.500  -0.1056   0.01787   0.01245  -0.1843   0.8349   0.0133
  -8.250  -0.0783   0.01687   0.01130  -0.1855   0.8266   0.0137
  -8.000  -0.0500   0.01619   0.01053  -0.1865   0.8194   0.0140
  -7.750  -0.0219   0.01558   0.00982  -0.1872   0.8119   0.0143
  -7.500   0.0072   0.01502   0.00914  -0.1881   0.8053   0.0146
  -7.250   0.0358   0.01446   0.00849  -0.1888   0.7983   0.0150
  -7.000   0.0651   0.01393   0.00785  -0.1895   0.7916   0.0155
  -6.750   0.0948   0.01345   0.00726  -0.1903   0.7855   0.0159
  -6.500   0.1244   0.01301   0.00673  -0.1910   0.7788   0.0163
  -6.250   0.1549   0.01252   0.00617  -0.1920   0.7727   0.0168
  -6.000   0.1851   0.01217   0.00578  -0.1928   0.7667   0.0174
  -5.750   0.2151   0.01188   0.00544  -0.1935   0.7602   0.0183
  -5.250   0.2763   0.01129   0.00471  -0.1950   0.7483   0.0201
  -5.000   0.3071   0.01100   0.00438  -0.1958   0.7420   0.0211
  -4.750   0.3377   0.01080   0.00411  -0.1965   0.7362   0.0224
  -4.500   0.3683   0.01058   0.00384  -0.1972   0.7300   0.0239
  -4.250   0.3989   0.01038   0.00361  -0.1978   0.7238   0.0262
  -4.000   0.4294   0.01022   0.00341  -0.1984   0.7180   0.0296
  -3.750   0.4600   0.01005   0.00323  -0.1991   0.7117   0.0346
  -3.500   0.4905   0.00990   0.00306  -0.1997   0.7054   0.0432
  -3.250   0.5214   0.00973   0.00293  -0.2004   0.6994   0.0609
  -3.000   0.5527   0.00953   0.00281  -0.2013   0.6929   0.0914
  -2.750   0.5840   0.00934   0.00269  -0.2023   0.6866   0.1339
  -2.500   0.6171   0.00903   0.00259  -0.2037   0.6803   0.2100
  -2.250   0.6499   0.00876   0.00254  -0.2051   0.6735   0.3037
  -2.000   0.6805   0.00867   0.00256  -0.2058   0.6674   0.3630
  -1.750   0.7102   0.00865   0.00259  -0.2061   0.6604   0.3977
  -1.500   0.7390   0.00870   0.00260  -0.2062   0.6537   0.4153
  -1.250   0.7679   0.00873   0.00263  -0.2064   0.6470   0.4297
  -1.000   0.7966   0.00878   0.00267  -0.2065   0.6398   0.4465
  -0.750   0.8251   0.00884   0.00272  -0.2066   0.6329   0.4664
  -0.500   0.8536   0.00890   0.00276  -0.2066   0.6255   0.4771
  -0.250   0.8815   0.00899   0.00281  -0.2066   0.6183   0.4857
   0.000   0.9099   0.00905   0.00286  -0.2066   0.6107   0.4935
   0.250   0.9376   0.00915   0.00292  -0.2065   0.6029   0.5012
   0.500   0.9657   0.00923   0.00298  -0.2065   0.5951   0.5091
   0.750   0.9932   0.00933   0.00306  -0.2064   0.5868   0.5164
   1.000   1.0210   0.00943   0.00314  -0.2063   0.5786   0.5246
   1.250   1.0481   0.00955   0.00324  -0.2061   0.5700   0.5319
   1.500   1.0757   0.00966   0.00334  -0.2060   0.5614   0.5397
   2.000   1.1298   0.00992   0.00357  -0.2057   0.5433   0.5556
   2.500   1.1833   0.01021   0.00384  -0.2052   0.5246   0.5715
   2.750   1.2096   0.01038   0.00399  -0.2049   0.5153   0.5803
   3.000   1.2359   0.01055   0.00415  -0.2046   0.5052   0.5885
   3.250   1.2621   0.01072   0.00432  -0.2043   0.4956   0.5970
   3.500   1.2876   0.01093   0.00451  -0.2038   0.4856   0.6057
   3.750   1.3130   0.01114   0.00471  -0.2034   0.4728   0.6152
   4.000   1.3371   0.01142   0.00494  -0.2027   0.4559   0.6239
   4.250   1.3600   0.01176   0.00520  -0.2018   0.4369   0.6331
   4.500   1.3831   0.01209   0.00548  -0.2010   0.4178   0.6427
   4.750   1.4056   0.01245   0.00577  -0.2000   0.3979   0.6526
   5.000   1.4278   0.01284   0.00611  -0.1991   0.3787   0.6626
   5.250   1.4500   0.01321   0.00643  -0.1981   0.3619   0.6725
   5.500   1.4719   0.01359   0.00678  -0.1971   0.3464   0.6837
   5.750   1.4936   0.01397   0.00714  -0.1961   0.3323   0.6946
   6.000   1.5146   0.01438   0.00752  -0.1949   0.3178   0.7058
   6.250   1.5345   0.01484   0.00794  -0.1936   0.3019   0.7180
   6.500   1.5527   0.01533   0.00839  -0.1919   0.2849   0.7303
   6.750   1.5694   0.01584   0.00887  -0.1900   0.2684   0.7428
   7.000   1.5856   0.01638   0.00938  -0.1880   0.2531   0.7564
   7.250   1.6011   0.01695   0.00992  -0.1859   0.2380   0.7711
   7.500   1.6159   0.01757   0.01052  -0.1838   0.2227   0.7867
   8.000   1.6412   0.01904   0.01193  -0.1790   0.1886   0.8222
   8.250   1.6515   0.01990   0.01275  -0.1763   0.1707   0.8450
   8.500   1.6598   0.02080   0.01364  -0.1733   0.1543   0.8766
   8.750   1.6619   0.02153   0.01440  -0.1690   0.1417   1.0000
   9.000   1.6719   0.02261   0.01542  -0.1667   0.1286   1.0000
   9.250   1.6823   0.02369   0.01647  -0.1645   0.1181   1.0000
   9.500   1.6922   0.02484   0.01760  -0.1624   0.1098   1.0000
   9.750   1.7026   0.02599   0.01875  -0.1604   0.1030   1.0000
  10.000   1.7127   0.02720   0.01997  -0.1585   0.0974   1.0000
  10.250   1.7231   0.02843   0.02123  -0.1567   0.0927   1.0000
  10.500   1.7317   0.02984   0.02265  -0.1548   0.0884   1.0000
  10.750   1.7424   0.03113   0.02399  -0.1533   0.0855   1.0000
  11.000   1.7526   0.03250   0.02541  -0.1517   0.0829   1.0000
  11.250   1.7614   0.03403   0.02698  -0.1502   0.0803   1.0000
  11.500   1.7690   0.03571   0.02870  -0.1487   0.0779   1.0000
  11.750   1.7766   0.03745   0.03051  -0.1472   0.0758   1.0000
  12.000   1.7859   0.03907   0.03220  -0.1460   0.0743   1.0000
  12.250   1.7941   0.04082   0.03403  -0.1448   0.0726   1.0000
  12.500   1.8011   0.04274   0.03601  -0.1436   0.0708   1.0000
  12.750   1.8071   0.04484   0.03817  -0.1425   0.0692   1.0000
  13.000   1.8120   0.04710   0.04050  -0.1414   0.0678   1.0000
  13.250   1.8152   0.04962   0.04308  -0.1403   0.0663   1.0000
  13.500   1.8207   0.05193   0.04548  -0.1395   0.0653   1.0000
  13.750   1.8271   0.05419   0.04784  -0.1387   0.0644   1.0000
  14.000   1.8324   0.05664   0.05038  -0.1381   0.0633   1.0000
  14.250   1.8368   0.05923   0.05307  -0.1375   0.0622   1.0000
  14.500   1.8407   0.06196   0.05589  -0.1370   0.0611   1.0000
  14.750   1.8434   0.06489   0.05890  -0.1366   0.0600   1.0000
  15.000   1.8448   0.06806   0.06214  -0.1363   0.0589   1.0000
  15.250   1.8446   0.07153   0.06569  -0.1361   0.0577   1.0000
  15.500   1.8441   0.07510   0.06934  -0.1360   0.0564   1.0000
  15.750   1.8490   0.07793   0.07228  -0.1360   0.0554   1.0000
  16.000   1.8527   0.08098   0.07543  -0.1361   0.0539   1.0000
  16.250   1.8545   0.08434   0.07888  -0.1363   0.0523   1.0000
  16.500   1.8548   0.08796   0.08257  -0.1366   0.0508   1.0000
  16.750   1.8532   0.09194   0.08662  -0.1371   0.0495   1.0000
<< Back to FX 63-137 13.7% smoothed (fx63137sm-il)

Polar data table (+)

Polar graphs


<< Back to FX 63-137 13.7% smoothed (fx63137sm-il)