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GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 628 AIRFOIL (goe628-il)
Reynolds number: 50,000
Max Cl/Cd: 27.45 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe628-il-50000-n5.txt
Download as CSV file: xf-goe628-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 628 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2604   0.11864   0.11160  -0.0418   1.0000   0.1087
 -10.500  -0.2710   0.11673   0.10979  -0.0404   1.0000   0.1084
 -10.250  -0.2838   0.11498   0.10814  -0.0386   1.0000   0.1078
 -10.000  -0.2759   0.11066   0.10382  -0.0425   0.9939   0.1072
  -9.750  -0.2639   0.10593   0.09907  -0.0477   0.9852   0.1080
  -9.500  -0.2537   0.10112   0.09422  -0.0529   0.9762   0.1086
  -9.250  -0.2435   0.09612   0.08919  -0.0584   0.9675   0.1086
  -9.000  -0.2381   0.09125   0.08431  -0.0630   0.9565   0.1082
  -8.750  -0.2353   0.08618   0.07922  -0.0679   0.9455   0.1084
  -8.500  -0.2357   0.08007   0.07309  -0.0744   0.9356   0.1092
  -8.250  -0.2548   0.07309   0.06609  -0.0804   0.9201   0.1096
  -8.000  -0.2975   0.05965   0.05237  -0.0929   0.9023   0.1096
  -7.750  -0.3180   0.05174   0.04394  -0.0982   0.8876   0.1102
  -7.500  -0.3073   0.04622   0.03777  -0.1026   0.8796   0.1115
  -7.250  -0.2981   0.04351   0.03468  -0.1027   0.8681   0.1127
  -7.000  -0.2643   0.04215   0.03328  -0.1045   0.8629   0.1152
  -6.750  -0.2505   0.04100   0.03201  -0.1034   0.8518   0.1174
  -6.500  -0.2216   0.03915   0.02986  -0.1049   0.8455   0.1207
  -6.250  -0.2039   0.03767   0.02805  -0.1044   0.8361   0.1235
  -6.000  -0.1772   0.03638   0.02659  -0.1048   0.8288   0.1263
  -5.750  -0.1451   0.03538   0.02554  -0.1057   0.8232   0.1302
  -5.500  -0.1289   0.03473   0.02476  -0.1042   0.8127   0.1344
  -5.250  -0.0960   0.03367   0.02358  -0.1053   0.8073   0.1412
  -5.000  -0.0781   0.03324   0.02313  -0.1039   0.7974   0.1476
  -4.750  -0.0484   0.03246   0.02231  -0.1043   0.7908   0.1571
  -4.500  -0.0200   0.03181   0.02165  -0.1043   0.7841   0.1704
  -4.250   0.0010   0.03157   0.02145  -0.1033   0.7747   0.1866
  -4.000   0.0365   0.03116   0.02103  -0.1042   0.7694   0.2120
  -3.750   0.0537   0.03132   0.02114  -0.1025   0.7589   0.2312
  -3.500   0.0865   0.03117   0.02090  -0.1028   0.7523   0.2534
  -3.250   0.1102   0.03138   0.02104  -0.1019   0.7435   0.2727
  -2.750   0.1729   0.03160   0.02118  -0.1017   0.7292   0.3164
  -2.500   0.1872   0.03195   0.02149  -0.0994   0.7171   0.3320
  -2.250   0.2242   0.03163   0.02104  -0.1000   0.7110   0.3510
  -2.000   0.2395   0.03185   0.02122  -0.0980   0.6992   0.3628
  -1.750   0.2746   0.03139   0.02063  -0.0985   0.6924   0.3757
  -1.500   0.2932   0.03146   0.02053  -0.0970   0.6814   0.3868
  -1.250   0.3240   0.03111   0.02014  -0.0969   0.6738   0.3972
  -1.000   0.3462   0.03109   0.01999  -0.0959   0.6641   0.4078
  -0.750   0.3735   0.03089   0.01972  -0.0954   0.6553   0.4177
  -0.500   0.4012   0.03075   0.01945  -0.0951   0.6467   0.4288
  -0.250   0.4250   0.03075   0.01937  -0.0942   0.6368   0.4389
   0.000   0.4580   0.03044   0.01895  -0.0946   0.6295   0.4504
   0.250   0.4767   0.03066   0.01910  -0.0932   0.6183   0.4613
   0.500   0.5120   0.03025   0.01861  -0.0938   0.6113   0.4734
   0.750   0.5280   0.03059   0.01894  -0.0920   0.5997   0.4846
   1.000   0.5639   0.03017   0.01842  -0.0927   0.5929   0.4995
   1.250   0.5782   0.03055   0.01887  -0.0907   0.5812   0.5108
   1.500   0.6136   0.03013   0.01840  -0.0913   0.5743   0.5284
   1.750   0.6275   0.03056   0.01891  -0.0893   0.5627   0.5437
   2.000   0.6628   0.03011   0.01845  -0.0898   0.5561   0.5665
   2.250   0.6747   0.03059   0.01910  -0.0876   0.5445   0.5886
   2.500   0.7096   0.02999   0.01863  -0.0879   0.5382   0.6328
   2.750   0.7182   0.03034   0.01943  -0.0851   0.5269   0.7063
   3.000   0.7707   0.02976   0.01889  -0.0887   0.5200   1.0000
   3.250   0.7791   0.03076   0.01981  -0.0863   0.5090   1.0000
   3.500   0.8125   0.03076   0.01956  -0.0867   0.5025   1.0000
   3.750   0.8213   0.03177   0.02052  -0.0843   0.4927   1.0000
   4.000   0.8494   0.03199   0.02056  -0.0841   0.4859   1.0000
   4.250   0.8647   0.03278   0.02128  -0.0825   0.4780   1.0000
   4.500   0.8822   0.03347   0.02189  -0.0812   0.4704   1.0000
   4.750   0.9175   0.03343   0.02165  -0.0818   0.4652   1.0000
   5.000   0.9137   0.03502   0.02331  -0.0781   0.4562   1.0000
   5.250   0.9387   0.03541   0.02360  -0.0776   0.4503   1.0000
   5.500   0.9626   0.03592   0.02401  -0.0770   0.4450   1.0000
   5.750   0.9558   0.03774   0.02590  -0.0732   0.4374   1.0000
   6.000   0.9812   0.03816   0.02625  -0.0728   0.4323   1.0000
   6.250   1.0076   0.03857   0.02657  -0.0725   0.4276   1.0000
   6.500   0.9859   0.04139   0.02952  -0.0678   0.4196   1.0000
   6.750   1.0085   0.04197   0.03005  -0.0672   0.4149   1.0000
   7.000   1.0475   0.04173   0.02970  -0.0679   0.4116   1.0000
   7.250   0.9922   0.04725   0.03546  -0.0621   0.4024   1.0000
   7.500   1.0072   0.04839   0.03659  -0.0611   0.3977   1.0000
   7.750   1.0451   0.04789   0.03601  -0.0613   0.3948   1.0000
   8.000   0.9569   0.05812   0.04650  -0.0576   0.3818   1.0000
   8.250   0.9801   0.05860   0.04696  -0.0569   0.3787   1.0000
   8.500   1.0136   0.05810   0.04642  -0.0564   0.3767   1.0000
   9.000   0.9481   0.07168   0.06021  -0.0558   0.3591   1.0000
  10.500   0.9051   0.09920   0.08803  -0.0583   0.3230   1.0000
  11.000   0.8715   0.11126   0.10023  -0.0610   0.3089   1.0000
  11.250   0.8923   0.11205   0.10103  -0.0605   0.3063   1.0000
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