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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 50,000
Max Cl/Cd: 45.32 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe123-il-50000-n5.txt
Download as CSV file: xf-goe123-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 123 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3108   0.10794   0.10137  -0.0274   1.0000   0.0684
  -7.500  -0.3182   0.10811   0.10167  -0.0283   1.0000   0.0690
  -7.250  -0.3233   0.10825   0.10190  -0.0300   1.0000   0.0693
  -7.000  -0.3197   0.10237   0.09610  -0.0261   1.0000   0.0706
  -6.750  -0.3181   0.09878   0.09255  -0.0233   1.0000   0.0725
  -6.500  -0.3191   0.09656   0.09039  -0.0221   1.0000   0.0741
  -6.250  -0.3197   0.09454   0.08843  -0.0215   1.0000   0.0759
  -6.000  -0.3190   0.09259   0.08652  -0.0215   1.0000   0.0780
  -5.750  -0.3157   0.09085   0.08482  -0.0228   1.0000   0.0804
  -5.500  -0.3041   0.09028   0.08421  -0.0283   1.0000   0.0826
  -5.250  -0.2916   0.08820   0.08211  -0.0319   1.0000   0.0835
  -5.000  -0.2948   0.08340   0.07740  -0.0269   1.0000   0.0855
  -4.750  -0.2851   0.08023   0.07424  -0.0268   0.9988   0.0896
  -4.500  -0.2282   0.07842   0.07210  -0.0420   0.9918   0.0974
  -4.250  -0.2102   0.07308   0.06681  -0.0430   0.9873   0.0992
  -4.000  -0.1865   0.06919   0.06288  -0.0454   0.9821   0.1035
  -3.750  -0.1335   0.06661   0.05999  -0.0565   0.9763   0.1122
  -3.500  -0.1151   0.06250   0.05590  -0.0570   0.9707   0.1182
  -3.000  -0.0384   0.05633   0.04939  -0.0681   0.9592   0.1325
  -2.750   0.0051   0.05362   0.04644  -0.0744   0.9533   0.1404
  -2.500   0.0457   0.05118   0.04376  -0.0795   0.9473   0.1526
  -2.250   0.0793   0.04841   0.04089  -0.0828   0.9415   0.1674
  -2.000   0.1158   0.04596   0.03829  -0.0865   0.9354   0.1825
  -1.750   0.1538   0.04367   0.03583  -0.0903   0.9298   0.1986
  -1.500   0.2161   0.04116   0.03249  -0.0959   0.9237   0.0946
  -1.250   0.2663   0.03901   0.02980  -0.1003   0.9193   0.0824
  -1.000   0.2994   0.03755   0.02808  -0.1019   0.9113   0.0824
  -0.750   0.3426   0.03609   0.02623  -0.1051   0.9059   0.0830
  -0.500   0.3758   0.03466   0.02464  -0.1067   0.8982   0.0819
  -0.250   0.4157   0.03328   0.02303  -0.1092   0.8919   0.0806
   0.000   0.4518   0.03219   0.02169  -0.1107   0.8842   0.0798
   0.250   0.4899   0.03114   0.02037  -0.1124   0.8767   0.0795
   0.500   0.5229   0.03030   0.01932  -0.1131   0.8672   0.0797
   0.750   0.5636   0.02931   0.01801  -0.1147   0.8596   0.0812
   1.250   0.6245   0.02817   0.01663  -0.1145   0.8358   0.0915
   1.500   0.6576   0.02744   0.01574  -0.1145   0.8253   0.0956
   1.750   0.6900   0.02674   0.01502  -0.1145   0.8148   0.1009
   2.250   0.7451   0.02594   0.01418  -0.1132   0.7891   0.1254
   2.500   0.7746   0.02535   0.01372  -0.1130   0.7766   0.1781
   2.750   0.7994   0.02358   0.01338  -0.1118   0.7643   1.0000
   3.000   0.8275   0.02353   0.01313  -0.1110   0.7508   1.0000
   3.250   0.8546   0.02351   0.01298  -0.1101   0.7363   1.0000
   3.500   0.8807   0.02352   0.01296  -0.1091   0.7206   1.0000
   3.750   0.9062   0.02356   0.01296  -0.1081   0.7037   1.0000
   4.000   0.9316   0.02360   0.01298  -0.1070   0.6859   1.0000
   4.250   0.9575   0.02361   0.01299  -0.1059   0.6675   1.0000
   4.500   0.9840   0.02359   0.01298  -0.1049   0.6486   1.0000
   4.750   1.0084   0.02372   0.01313  -0.1037   0.6269   1.0000
   5.000   1.0338   0.02381   0.01321  -0.1026   0.6050   1.0000
   5.250   1.0589   0.02397   0.01338  -0.1014   0.5823   1.0000
   5.500   1.0837   0.02420   0.01359  -0.1003   0.5596   1.0000
   5.750   1.1082   0.02454   0.01390  -0.0992   0.5375   1.0000
   6.000   1.1318   0.02501   0.01438  -0.0981   0.5157   1.0000
   6.250   1.1560   0.02551   0.01491  -0.0971   0.4958   1.0000
   6.500   1.1790   0.02615   0.01561  -0.0962   0.4764   1.0000
   6.750   1.2015   0.02684   0.01639  -0.0952   0.4575   1.0000
   7.000   1.2237   0.02753   0.01718  -0.0942   0.4388   1.0000
   7.250   1.2454   0.02823   0.01800  -0.0930   0.4202   1.0000
   7.500   1.2661   0.02897   0.01883  -0.0917   0.4016   1.0000
   7.750   1.2842   0.02978   0.01978  -0.0902   0.3810   1.0000
   8.000   1.3000   0.03052   0.02054  -0.0883   0.3575   1.0000
   8.250   1.3122   0.03139   0.02157  -0.0860   0.3316   1.0000
   8.500   1.3225   0.03234   0.02258  -0.0836   0.3050   1.0000
   8.750   1.3291   0.03341   0.02371  -0.0808   0.2746   1.0000
   9.000   1.3331   0.03466   0.02500  -0.0780   0.2400   1.0000
   9.250   1.3339   0.03618   0.02648  -0.0749   0.1991   1.0000
   9.500   1.3308   0.03828   0.02835  -0.0718   0.1523   1.0000
   9.750   1.3251   0.04111   0.03084  -0.0690   0.1091   1.0000
  10.000   1.3181   0.04434   0.03380  -0.0665   0.0892   1.0000
  10.250   1.3118   0.04763   0.03702  -0.0643   0.0778   1.0000
  10.500   1.3067   0.05089   0.04036  -0.0625   0.0702   1.0000
  10.750   1.3040   0.05402   0.04369  -0.0608   0.0647   1.0000
  11.000   1.3015   0.05719   0.04701  -0.0595   0.0597   1.0000
  11.250   1.2976   0.06058   0.05047  -0.0585   0.0560   1.0000
  11.500   1.2973   0.06370   0.05384  -0.0575   0.0522   1.0000
  11.750   1.2959   0.06700   0.05728  -0.0567   0.0495   1.0000
  12.000   1.2949   0.07029   0.06067  -0.0559   0.0477   1.0000
  12.250   1.2961   0.07340   0.06387  -0.0548   0.0459   1.0000
  12.500   1.2996   0.07652   0.06730  -0.0538   0.0437   1.0000
  12.750   1.3002   0.08001   0.07105  -0.0532   0.0417   1.0000
  13.000   1.2989   0.08373   0.07497  -0.0530   0.0400   1.0000
  13.250   1.2974   0.08752   0.07893  -0.0530   0.0387   1.0000
  13.500   1.2970   0.09135   0.08292  -0.0528   0.0377   1.0000
  13.750   1.2962   0.09546   0.08725  -0.0527   0.0370   1.0000
  14.000   1.2912   0.10032   0.09230  -0.0533   0.0365   1.0000
  14.250   1.2796   0.10622   0.09848  -0.0554   0.0364   1.0000
  14.500   1.2663   0.11268   0.10521  -0.0582   0.0363   1.0000
  14.750   1.2518   0.11973   0.11250  -0.0618   0.0363   1.0000
  15.000   1.2368   0.12733   0.12031  -0.0661   0.0364   1.0000
  15.250   1.2218   0.13546   0.12863  -0.0710   0.0365   1.0000
  15.500   1.2004   0.14635   0.13974  -0.0785   0.0371   1.0000
  15.750   1.1616   0.16572   0.15932  -0.0919   0.0390   1.0000
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