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GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il)
Reynolds number: 100,000
Max Cl/Cd: 58.99 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe174-il-100000-n5.txt
Download as CSV file: xf-goe174-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2796   0.09342   0.08906  -0.0256   1.0000   0.0418
  -7.000  -0.2844   0.09158   0.08732  -0.0246   1.0000   0.0427
  -6.750  -0.2908   0.08990   0.08574  -0.0236   1.0000   0.0437
  -6.500  -0.2509   0.08521   0.08099  -0.0423   0.9874   0.0469
  -6.250  -0.2263   0.07970   0.07545  -0.0485   0.9785   0.0478
  -6.000  -0.2128   0.07642   0.07220  -0.0453   0.9720   0.0508
  -5.750  -0.1552   0.07190   0.06743  -0.0663   0.9565   0.0587
  -5.500  -0.1436   0.06694   0.06257  -0.0646   0.9485   0.0603
  -5.250  -0.1194   0.06347   0.05909  -0.0662   0.9404   0.0634
  -5.000  -0.0604   0.05839   0.05363  -0.0827   0.9285   0.0726
  -4.750  -0.0468   0.05500   0.05037  -0.0802   0.9201   0.0761
  -4.500   0.0090   0.05058   0.04551  -0.0925   0.9103   0.0879
  -4.250   0.0340   0.04674   0.04169  -0.0938   0.8995   0.0897
  -4.000   0.0768   0.04138   0.03601  -0.0997   0.8898   0.0753
  -3.750   0.1225   0.03481   0.02888  -0.1054   0.8797   0.0523
  -3.500   0.1671   0.02905   0.02209  -0.1098   0.8679   0.0478
  -3.250   0.1982   0.02735   0.02029  -0.1112   0.8525   0.0503
  -3.000   0.2321   0.02504   0.01746  -0.1125   0.8357   0.0505
  -2.750   0.2647   0.02304   0.01488  -0.1132   0.8180   0.0499
  -2.500   0.2952   0.02162   0.01301  -0.1134   0.8002   0.0499
  -2.250   0.3235   0.02064   0.01175  -0.1133   0.7825   0.0512
  -2.000   0.3518   0.01985   0.01072  -0.1131   0.7659   0.0534
  -1.750   0.3801   0.01903   0.00964  -0.1128   0.7495   0.0539
  -1.500   0.4081   0.01832   0.00872  -0.1125   0.7335   0.0542
  -1.250   0.4358   0.01774   0.00796  -0.1121   0.7179   0.0548
  -1.000   0.4633   0.01725   0.00733  -0.1117   0.7027   0.0555
  -0.750   0.4906   0.01686   0.00680  -0.1113   0.6882   0.0565
  -0.500   0.5178   0.01658   0.00638  -0.1109   0.6745   0.0580
  -0.250   0.5449   0.01631   0.00601  -0.1105   0.6613   0.0617
   0.000   0.5719   0.01618   0.00574  -0.1101   0.6487   0.0656
   0.250   0.5987   0.01610   0.00552  -0.1096   0.6360   0.0690
   0.500   0.6260   0.01605   0.00537  -0.1092   0.6235   0.0748
   0.750   0.6533   0.01595   0.00528  -0.1089   0.6112   0.0979
   1.000   0.6802   0.01562   0.00540  -0.1089   0.5993   0.2808
   1.500   0.7315   0.01450   0.00544  -0.1076   0.5750   1.0000
   1.750   0.7578   0.01472   0.00550  -0.1071   0.5620   1.0000
   2.000   0.7839   0.01494   0.00558  -0.1067   0.5489   1.0000
   2.250   0.8099   0.01517   0.00569  -0.1062   0.5358   1.0000
   2.500   0.8358   0.01540   0.00580  -0.1058   0.5230   1.0000
   2.750   0.8615   0.01563   0.00593  -0.1053   0.5100   1.0000
   3.000   0.8871   0.01588   0.00609  -0.1048   0.4966   1.0000
   3.250   0.9125   0.01613   0.00627  -0.1043   0.4831   1.0000
   3.500   0.9379   0.01641   0.00648  -0.1038   0.4703   1.0000
   3.750   0.9632   0.01671   0.00672  -0.1033   0.4586   1.0000
   4.000   0.9884   0.01703   0.00697  -0.1028   0.4483   1.0000
   4.250   1.0135   0.01737   0.00725  -0.1023   0.4378   1.0000
   4.500   1.0386   0.01772   0.00760  -0.1019   0.4277   1.0000
   4.750   1.0633   0.01809   0.00791  -0.1013   0.4183   1.0000
   5.000   1.0879   0.01846   0.00828  -0.1008   0.4086   1.0000
   5.250   1.1125   0.01886   0.00867  -0.1003   0.3998   1.0000
   5.500   1.1368   0.01927   0.00908  -0.0997   0.3915   1.0000
   5.750   1.1610   0.01968   0.00954  -0.0992   0.3828   1.0000
   6.000   1.1851   0.02013   0.00995  -0.0986   0.3756   1.0000
   6.250   1.2091   0.02055   0.01050  -0.0981   0.3673   1.0000
   6.500   1.2324   0.02101   0.01094  -0.0974   0.3594   1.0000
   6.750   1.2554   0.02145   0.01149  -0.0967   0.3500   1.0000
   7.000   1.2781   0.02192   0.01200  -0.0960   0.3418   1.0000
   7.250   1.3007   0.02238   0.01259  -0.0952   0.3335   1.0000
   7.500   1.3233   0.02289   0.01318  -0.0945   0.3266   1.0000
   7.750   1.3460   0.02339   0.01385  -0.0938   0.3202   1.0000
   8.000   1.3684   0.02394   0.01444  -0.0930   0.3146   1.0000
   8.250   1.3899   0.02446   0.01523  -0.0921   0.3072   1.0000
   8.500   1.4099   0.02498   0.01583  -0.0910   0.2983   1.0000
   8.750   1.4273   0.02547   0.01645  -0.0895   0.2851   1.0000
   9.000   1.4435   0.02599   0.01710  -0.0879   0.2700   1.0000
   9.250   1.4590   0.02656   0.01781  -0.0862   0.2542   1.0000
   9.500   1.4735   0.02720   0.01864  -0.0844   0.2340   1.0000
   9.750   1.4848   0.02803   0.01950  -0.0823   0.2097   1.0000
  10.000   1.4912   0.02921   0.02059  -0.0797   0.1733   1.0000
  10.250   1.4853   0.03109   0.02219  -0.0756   0.1362   1.0000
  10.500   1.4782   0.03336   0.02430  -0.0719   0.1077   1.0000
  10.750   1.4633   0.03645   0.02713  -0.0683   0.0634   1.0000
  11.000   1.4501   0.03971   0.03034  -0.0655   0.0532   1.0000
  11.250   1.4381   0.04318   0.03393  -0.0636   0.0467   1.0000
  11.500   1.4302   0.04655   0.03750  -0.0623   0.0409   1.0000
  11.750   1.4190   0.05055   0.04168  -0.0617   0.0373   1.0000
  12.000   1.4092   0.05468   0.04602  -0.0616   0.0344   1.0000
  12.250   1.3987   0.05919   0.05073  -0.0620   0.0321   1.0000
  12.500   1.3860   0.06419   0.05589  -0.0628   0.0305   1.0000
  12.750   1.3714   0.06965   0.06150  -0.0639   0.0295   1.0000
  13.000   1.3575   0.07517   0.06718  -0.0652   0.0285   1.0000
  13.250   1.3434   0.08086   0.07305  -0.0666   0.0277   1.0000
  13.500   1.3296   0.08668   0.07903  -0.0683   0.0268   1.0000
  13.750   1.3166   0.09251   0.08501  -0.0700   0.0260   1.0000
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