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GOE 625 AIRFOIL (goe625-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 625 AIRFOIL (goe625-il)
Reynolds number: 50,000
Max Cl/Cd: 18.81 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe625-il-50000-n5.txt
Download as CSV file: xf-goe625-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 625 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1057   0.11113   0.10375  -0.0832   0.9275   0.1192
  -9.500  -0.0949   0.10659   0.09917  -0.0875   0.9205   0.1200
  -9.250  -0.0877   0.10219   0.09474  -0.0914   0.9134   0.1215
  -9.000  -0.0892   0.09811   0.09065  -0.0939   0.9039   0.1225
  -8.750  -0.0868   0.09286   0.08535  -0.0987   0.8982   0.1233
  -8.500  -0.1064   0.08924   0.08177  -0.0990   0.8853   0.1240
  -8.250  -0.1308   0.08400   0.07650  -0.1017   0.8748   0.1246
  -8.000  -0.1615   0.07785   0.07026  -0.1044   0.8630   0.1250
  -7.750  -0.1941   0.07263   0.06487  -0.1043   0.8502   0.1255
  -7.500  -0.1726   0.07066   0.06288  -0.1051   0.8435   0.1274
  -7.250  -0.1702   0.06858   0.06074  -0.1040   0.8333   0.1291
  -7.000  -0.1665   0.06518   0.05717  -0.1046   0.8246   0.1310
  -6.750  -0.1705   0.06188   0.05365  -0.1038   0.8140   0.1325
  -6.500  -0.1659   0.05809   0.04950  -0.1042   0.8052   0.1348
  -6.250  -0.1655   0.05465   0.04558  -0.1034   0.7949   0.1372
  -6.000  -0.1491   0.05202   0.04262  -0.1035   0.7864   0.1392
  -5.750  -0.1238   0.05054   0.04106  -0.1036   0.7790   0.1412
  -5.500  -0.1078   0.04930   0.03970  -0.1024   0.7681   0.1436
  -5.250  -0.0753   0.04704   0.03711  -0.1041   0.7633   0.1472
  -5.000  -0.0675   0.04581   0.03559  -0.1017   0.7497   0.1494
  -4.750  -0.0342   0.04340   0.03262  -0.1032   0.7446   0.1526
  -4.500  -0.0217   0.04288   0.03212  -0.1010   0.7312   0.1547
  -4.250   0.0146   0.04152   0.03064  -0.1023   0.7258   0.1585
  -4.000   0.0284   0.04094   0.02991  -0.1003   0.7126   0.1614
  -3.750   0.0651   0.03935   0.02796  -0.1016   0.7070   0.1656
  -3.500   0.0805   0.03881   0.02718  -0.0998   0.6941   0.1688
  -3.250   0.1165   0.03771   0.02607  -0.1008   0.6884   0.1736
  -3.000   0.1327   0.03749   0.02576  -0.0992   0.6761   0.1780
  -2.750   0.1687   0.03642   0.02438  -0.1001   0.6701   0.1847
  -2.500   0.1869   0.03616   0.02413  -0.0987   0.6588   0.1889
  -2.250   0.2204   0.03537   0.02325  -0.0993   0.6522   0.1968
  -2.000   0.2427   0.03515   0.02287  -0.0984   0.6425   0.2051
  -1.750   0.2719   0.03463   0.02236  -0.0984   0.6350   0.2141
  -1.500   0.3110   0.03379   0.02135  -0.0997   0.6304   0.2266
  -1.250   0.3223   0.03424   0.02184  -0.0976   0.6194   0.2357
  -1.000   0.3565   0.03370   0.02123  -0.0983   0.6142   0.2506
  -0.750   0.3775   0.03383   0.02133  -0.0975   0.6066   0.2651
  -0.500   0.4004   0.03385   0.02137  -0.0968   0.5993   0.2835
  -0.250   0.4343   0.03330   0.02092  -0.0976   0.5948   0.3108
   0.000   0.4493   0.03370   0.02146  -0.0961   0.5871   0.3355
   0.250   0.4710   0.03373   0.02167  -0.0954   0.5809   0.3714
   0.500   0.5013   0.03315   0.02143  -0.0956   0.5768   0.4406
   0.750   0.5210   0.03255   0.02164  -0.0936   0.5727   0.6099
   1.000   0.5519   0.03309   0.02287  -0.0938   0.5652   0.9679
   1.250   0.5813   0.03340   0.02288  -0.0943   0.5604   1.0000
   1.500   0.6157   0.03339   0.02256  -0.0952   0.5570   1.0000
   1.750   0.6144   0.03485   0.02394  -0.0917   0.5502   1.0000
   2.000   0.6208   0.03602   0.02500  -0.0891   0.5444   1.0000
   2.250   0.6475   0.03641   0.02519  -0.0891   0.5408   1.0000
   2.500   0.6846   0.03640   0.02495  -0.0904   0.5380   1.0000
   2.750   0.6536   0.03949   0.02813  -0.0838   0.5296   1.0000
   3.000   0.6636   0.04080   0.02935  -0.0821   0.5243   1.0000
   3.250   0.6933   0.04103   0.02942  -0.0824   0.5213   1.0000
   3.500   0.7317   0.04085   0.02904  -0.0836   0.5190   1.0000
   4.000   0.6901   0.04790   0.03622  -0.0756   0.5031   1.0000
   4.250   0.7254   0.04761   0.03577  -0.0761   0.5009   1.0000
   4.500   0.7661   0.04702   0.03502  -0.0770   0.4992   1.0000
   5.000   0.7226   0.05552   0.04365  -0.0711   0.4816   1.0000
   5.500   0.6985   0.06361   0.05181  -0.0681   0.4640   1.0000
   5.750   0.7072   0.06567   0.05382  -0.0673   0.4584   1.0000
   7.750   0.7482   0.08542   0.07349  -0.0622   0.4050   1.0000
   8.000   0.7219   0.09156   0.07971  -0.0617   0.3930   1.0000
   8.250   0.7393   0.09270   0.08082  -0.0613   0.3885   1.0000
   8.500   0.7654   0.09285   0.08093  -0.0609   0.3859   1.0000
   9.000   0.7540   0.10073   0.08888  -0.0606   0.3700   1.0000
   9.250   0.7786   0.10107   0.08917  -0.0603   0.3676   1.0000
   9.750   0.7688   0.10889   0.09706  -0.0604   0.3524   1.0000
  10.000   0.7916   0.10944   0.09758  -0.0601   0.3501   1.0000
  10.500   0.7759   0.11856   0.10680  -0.0610   0.3366   1.0000
  10.750   0.7964   0.11944   0.10765  -0.0608   0.3341   1.0000
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