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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 500,000
Max Cl/Cd: 101.92 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe174-il-500000-n5.txt
Download as CSV file: xf-goe174-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 174 (ALBATROS 5020) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2972   0.10364   0.10140  -0.0266   1.0000   0.0082
  -9.000  -0.2958   0.10026   0.09803  -0.0272   1.0000   0.0083
  -8.750  -0.2959   0.09677   0.09458  -0.0278   1.0000   0.0084
  -8.250  -0.2790   0.09123   0.08909  -0.0311   0.9964   0.0087
  -7.750  -0.2487   0.08502   0.08289  -0.0379   0.9758   0.0095
  -7.500  -0.2308   0.08070   0.07856  -0.0434   0.9478   0.0099
  -7.250  -0.1998   0.07479   0.07259  -0.0536   0.9241   0.0102
  -7.000  -0.1753   0.06915   0.06682  -0.0622   0.8968   0.0105
  -6.750  -0.1555   0.06152   0.05905  -0.0725   0.8744   0.0111
  -6.500  -0.1343   0.05887   0.05630  -0.0761   0.8568   0.0114
  -6.250  -0.1126   0.05675   0.05407  -0.0790   0.8397   0.0118
  -6.000  -0.0887   0.05345   0.05067  -0.0834   0.8230   0.0126
  -5.750  -0.0597   0.04766   0.04470  -0.0908   0.8073   0.0134
  -5.500  -0.0239   0.03889   0.03564  -0.1008   0.7927   0.0146
  -5.000   0.0410   0.02265   0.01827  -0.1117   0.7571   0.0184
  -4.750   0.0658   0.02221   0.01763  -0.1116   0.7220   0.0188
  -4.500   0.0904   0.02189   0.01707  -0.1113   0.6833   0.0193
  -4.250   0.1167   0.02038   0.01520  -0.1116   0.6611   0.0204
  -4.000   0.1446   0.01788   0.01212  -0.1120   0.6465   0.0218
  -3.750   0.1725   0.01666   0.01039  -0.1120   0.6339   0.0231
  -3.500   0.1993   0.01564   0.00921  -0.1122   0.6230   0.0237
  -3.250   0.2266   0.01498   0.00840  -0.1122   0.6140   0.0242
  -3.000   0.2541   0.01438   0.00763  -0.1121   0.6060   0.0247
  -2.750   0.2819   0.01383   0.00693  -0.1121   0.5984   0.0253
  -2.500   0.3096   0.01341   0.00636  -0.1120   0.5901   0.0263
  -2.250   0.3375   0.01291   0.00571  -0.1120   0.5825   0.0268
  -2.000   0.3653   0.01248   0.00515  -0.1119   0.5749   0.0273
  -1.750   0.3933   0.01212   0.00468  -0.1118   0.5680   0.0277
  -1.500   0.4211   0.01181   0.00429  -0.1117   0.5599   0.0280
  -1.250   0.4488   0.01154   0.00394  -0.1116   0.5516   0.0283
  -1.000   0.4764   0.01137   0.00369  -0.1114   0.5418   0.0286
  -0.750   0.5041   0.01119   0.00345  -0.1113   0.5301   0.0291
  -0.500   0.5315   0.01086   0.00307  -0.1112   0.5174   0.0294
  -0.250   0.5588   0.01064   0.00279  -0.1110   0.5024   0.0297
   0.000   0.5861   0.01050   0.00257  -0.1109   0.4863   0.0302
   0.250   0.6132   0.01041   0.00241  -0.1107   0.4700   0.0308
   0.500   0.6403   0.01039   0.00231  -0.1106   0.4528   0.0315
   0.750   0.6673   0.01041   0.00225  -0.1104   0.4363   0.0322
   1.250   0.7212   0.01054   0.00222  -0.1100   0.4055   0.0338
   1.500   0.7481   0.01063   0.00224  -0.1098   0.3914   0.0349
   1.750   0.7749   0.01074   0.00228  -0.1096   0.3782   0.0363
   2.250   0.8284   0.01099   0.00240  -0.1092   0.3543   0.0393
   2.500   0.8551   0.01112   0.00250  -0.1089   0.3444   0.0456
   2.750   0.8822   0.01099   0.00269  -0.1090   0.3371   0.2046
   3.750   0.9849   0.01019   0.00337  -0.1077   0.3067   1.0000
   4.000   1.0112   0.01040   0.00353  -0.1075   0.3005   1.0000
   4.250   1.0378   0.01057   0.00368  -0.1073   0.2944   1.0000
   4.500   1.0640   0.01077   0.00386  -0.1070   0.2876   1.0000
   4.750   1.0902   0.01097   0.00404  -0.1068   0.2819   1.0000
   5.000   1.1165   0.01116   0.00422  -0.1066   0.2755   1.0000
   5.250   1.1423   0.01139   0.00443  -0.1063   0.2696   1.0000
   5.500   1.1685   0.01156   0.00463  -0.1060   0.2644   1.0000
   5.750   1.1943   0.01178   0.00484  -0.1057   0.2576   1.0000
   6.000   1.2198   0.01201   0.00508  -0.1054   0.2518   1.0000
   6.250   1.2455   0.01222   0.00531  -0.1051   0.2452   1.0000
   6.500   1.2700   0.01255   0.00558  -0.1047   0.2305   1.0000
   6.750   1.2928   0.01302   0.00592  -0.1040   0.2048   1.0000
   7.000   1.3113   0.01393   0.00653  -0.1028   0.1550   1.0000
   7.250   1.3303   0.01477   0.00718  -0.1016   0.1252   1.0000
   7.500   1.3517   0.01533   0.00770  -0.1007   0.1128   1.0000
   7.750   1.3734   0.01585   0.00820  -0.0998   0.1017   1.0000
   8.000   1.3917   0.01668   0.00888  -0.0985   0.0660   1.0000
   8.250   1.4087   0.01758   0.00970  -0.0970   0.0506   1.0000
   8.500   1.4288   0.01815   0.01031  -0.0959   0.0439   1.0000
   8.750   1.4480   0.01878   0.01095  -0.0947   0.0344   1.0000
   9.000   1.4621   0.01979   0.01185  -0.0929   0.0165   1.0000
   9.250   1.4788   0.02054   0.01265  -0.0913   0.0137   1.0000
   9.500   1.4946   0.02130   0.01348  -0.0896   0.0118   1.0000
   9.750   1.5104   0.02198   0.01424  -0.0879   0.0109   1.0000
  10.000   1.5227   0.02273   0.01508  -0.0856   0.0101   1.0000
  10.250   1.5327   0.02362   0.01604  -0.0831   0.0094   1.0000
  10.500   1.5399   0.02472   0.01725  -0.0803   0.0088   1.0000
  10.750   1.5479   0.02580   0.01843  -0.0779   0.0084   1.0000
  11.000   1.5565   0.02690   0.01963  -0.0757   0.0080   1.0000
  11.250   1.5638   0.02815   0.02097  -0.0736   0.0075   1.0000
  11.500   1.5697   0.02960   0.02252  -0.0717   0.0071   1.0000
  11.750   1.5746   0.03122   0.02424  -0.0700   0.0068   1.0000
  12.000   1.5775   0.03317   0.02629  -0.0685   0.0066   1.0000
  12.250   1.5776   0.03550   0.02874  -0.0671   0.0063   1.0000
  12.500   1.5740   0.03839   0.03176  -0.0660   0.0061   1.0000
  12.750   1.5690   0.04163   0.03512  -0.0652   0.0060   1.0000
  13.000   1.5672   0.04472   0.03835  -0.0649   0.0059   1.0000
  13.250   1.5635   0.04822   0.04198  -0.0649   0.0058   1.0000
  13.500   1.5581   0.05207   0.04596  -0.0651   0.0057   1.0000
  13.750   1.5511   0.05622   0.05025  -0.0655   0.0055   1.0000
  14.000   1.5423   0.06064   0.05481  -0.0661   0.0055   1.0000
  14.250   1.5321   0.06532   0.05961  -0.0667   0.0054   1.0000
  14.500   1.5215   0.07020   0.06462  -0.0675   0.0053   1.0000
  14.750   1.5102   0.07527   0.06982  -0.0685   0.0052   1.0000
  15.000   1.4989   0.08046   0.07513  -0.0697   0.0052   1.0000
  15.250   1.4879   0.08573   0.08052  -0.0709   0.0051   1.0000
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