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GOE 123 AIRFOIL (goe123-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 123 AIRFOIL (goe123-il)
Reynolds number: 100,000
Max Cl/Cd: 65.76 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe123-il-100000.txt
Download as CSV file: xf-goe123-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3083   0.10234   0.09762  -0.0264   1.0000   0.0495
  -7.500  -0.3197   0.10239   0.09778  -0.0251   1.0000   0.0499
  -7.250  -0.3291   0.10256   0.09803  -0.0252   1.0000   0.0502
  -7.000  -0.3347   0.10263   0.09817  -0.0266   1.0000   0.0505
  -6.750  -0.3344   0.10234   0.09788  -0.0293   1.0000   0.0506
  -6.500  -0.3356   0.09762   0.09325  -0.0266   1.0000   0.0511
  -6.250  -0.3377   0.09247   0.08816  -0.0209   1.0000   0.0520
  -6.000  -0.3380   0.08957   0.08530  -0.0186   1.0000   0.0530
  -5.750  -0.3368   0.08720   0.08295  -0.0177   1.0000   0.0542
  -5.500  -0.3335   0.08492   0.08070  -0.0177   1.0000   0.0557
  -5.250  -0.3274   0.08265   0.07844  -0.0187   1.0000   0.0579
  -5.000  -0.3107   0.08106   0.07680  -0.0233   1.0000   0.0615
  -4.750  -0.2714   0.08093   0.07644  -0.0354   1.0000   0.0632
  -4.500  -0.2754   0.07555   0.07118  -0.0312   1.0000   0.0640
  -4.250  -0.2720   0.07200   0.06766  -0.0291   1.0000   0.0653
  -4.000  -0.2609   0.06917   0.06484  -0.0293   1.0000   0.0674
  -3.750  -0.2384   0.06637   0.06198  -0.0324   0.9991   0.0709
  -3.500  -0.1669   0.06341   0.05867  -0.0473   0.9935   0.0774
  -3.250  -0.1472   0.05892   0.05423  -0.0483   0.9886   0.0807
  -3.000  -0.0676   0.05861   0.05335  -0.0622   0.9828   0.0909
  -2.750  -0.0519   0.05283   0.04775  -0.0629   0.9776   0.0928
  -2.500  -0.0153   0.04971   0.04458  -0.0670   0.9724   0.0987
  -2.250   0.0341   0.04723   0.04183  -0.0737   0.9668   0.1076
  -2.000   0.0844   0.04623   0.04047  -0.0796   0.9598   0.1198
  -1.750   0.1207   0.04222   0.03654  -0.0835   0.9559   0.1252
  -1.500   0.1604   0.04055   0.03464  -0.0872   0.9480   0.1354
  -1.250   0.2078   0.03851   0.03239  -0.0922   0.9426   0.1484
  -1.000   0.2459   0.03661   0.03037  -0.0954   0.9354   0.1625
  -0.750   0.2902   0.03478   0.02840  -0.0996   0.9287   0.1893
  -0.500   0.3308   0.03283   0.02637  -0.1029   0.9206   0.2205
  -0.250   0.3769   0.03068   0.02419  -0.1071   0.9131   0.2791
   0.000   0.4172   0.02889   0.02235  -0.1098   0.9036   0.3230
   0.500   0.5306   0.02774   0.01981  -0.1153   0.8877   0.1334
   0.750   0.5802   0.02581   0.01767  -0.1184   0.8824   0.1167
   1.000   0.6140   0.02472   0.01640  -0.1187   0.8720   0.1088
   1.250   0.6586   0.02357   0.01498  -0.1203   0.8662   0.1049
   1.500   0.6877   0.02274   0.01415  -0.1199   0.8543   0.1058
   1.750   0.7183   0.02195   0.01341  -0.1196   0.8433   0.1098
   2.000   0.7539   0.02100   0.01251  -0.1196   0.8359   0.1228
   2.250   0.7809   0.02037   0.01191  -0.1184   0.8229   0.1387
   2.500   0.8098   0.01919   0.01099  -0.1177   0.8102   0.2388
   2.750   0.8341   0.01761   0.01051  -0.1157   0.7973   1.0000
   3.000   0.8614   0.01735   0.01014  -0.1144   0.7831   1.0000
   3.250   0.8884   0.01706   0.00977  -0.1131   0.7679   1.0000
   3.500   0.9153   0.01675   0.00938  -0.1117   0.7513   1.0000
   3.750   0.9424   0.01642   0.00897  -0.1103   0.7335   1.0000
   4.000   0.9672   0.01629   0.00882  -0.1088   0.7115   1.0000
   4.250   0.9933   0.01612   0.00858  -0.1075   0.6896   1.0000
   4.500   1.0180   0.01613   0.00854  -0.1062   0.6638   1.0000
   4.750   1.0429   0.01618   0.00851  -0.1049   0.6371   1.0000
   5.000   1.0675   0.01633   0.00858  -0.1037   0.6086   1.0000
   5.250   1.0916   0.01660   0.00872  -0.1024   0.5792   1.0000
   5.500   1.1154   0.01700   0.00897  -0.1013   0.5507   1.0000
   5.750   1.1391   0.01750   0.00932  -0.1002   0.5240   1.0000
   6.000   1.1623   0.01806   0.00984  -0.0992   0.4985   1.0000
   6.250   1.1855   0.01867   0.01041  -0.0983   0.4756   1.0000
   6.500   1.2079   0.01922   0.01088  -0.0971   0.4518   1.0000
   6.750   1.2286   0.01972   0.01137  -0.0958   0.4254   1.0000
   7.000   1.2492   0.02024   0.01192  -0.0945   0.4009   1.0000
   7.250   1.2691   0.02078   0.01239  -0.0932   0.3766   1.0000
   7.500   1.2878   0.02130   0.01299  -0.0917   0.3502   1.0000
   7.750   1.3051   0.02186   0.01358  -0.0900   0.3217   1.0000
   8.000   1.3206   0.02248   0.01422  -0.0881   0.2884   1.0000
   8.250   1.3308   0.02336   0.01503  -0.0855   0.2184   1.0000
   8.500   1.3250   0.02653   0.01708  -0.0812   0.1027   1.0000
   8.750   1.3271   0.02900   0.01934  -0.0778   0.0837   1.0000
   9.000   1.3321   0.03102   0.02141  -0.0746   0.0744   1.0000
   9.250   1.3342   0.03316   0.02348  -0.0714   0.0679   1.0000
   9.500   1.3447   0.03479   0.02525  -0.0688   0.0633   1.0000
   9.750   1.3566   0.03663   0.02713  -0.0667   0.0596   1.0000
  10.000   1.3780   0.03937   0.02971  -0.0659   0.0558   1.0000
  10.250   1.3951   0.04111   0.03172  -0.0643   0.0529   1.0000
  10.500   1.4164   0.04338   0.03418  -0.0634   0.0503   1.0000
  10.750   1.4411   0.04625   0.03722  -0.0630   0.0487   1.0000
  11.000   1.4625   0.04950   0.04070  -0.0622   0.0478   1.0000
  11.250   1.4787   0.05306   0.04448  -0.0611   0.0468   1.0000
  11.500   1.4900   0.05828   0.05000  -0.0602   0.0456   1.0000
  11.750   1.4852   0.06140   0.05351  -0.0569   0.0452   1.0000
  12.000   1.4766   0.06448   0.05695  -0.0534   0.0450   1.0000
  12.250   1.4671   0.06820   0.06098  -0.0503   0.0451   1.0000
  12.500   1.4573   0.07256   0.06562  -0.0479   0.0454   1.0000
  12.750   1.4458   0.07658   0.06993  -0.0456   0.0457   1.0000
  13.000   1.4282   0.07958   0.07321  -0.0434   0.0460   1.0000
  13.250   1.4057   0.08328   0.07723  -0.0420   0.0464   1.0000
  13.500   1.3774   0.08816   0.08244  -0.0419   0.0470   1.0000
  13.750   1.3408   0.09465   0.08927  -0.0439   0.0476   1.0000
  14.000   1.3023   0.10284   0.09778  -0.0481   0.0483   1.0000
  14.250   1.2578   0.11393   0.10913  -0.0555   0.0496   1.0000
  14.500   1.2127   0.12815   0.12355  -0.0655   0.0523   1.0000
  14.750   1.1877   0.13952   0.13496  -0.0726   0.0541   1.0000
  15.000   1.1746   0.14838   0.14384  -0.0772   0.0553   1.0000
  15.250   0.8867   0.15398   0.14959  -0.0648   0.0658   1.0000
  15.500   0.8821   0.15871   0.15433  -0.0662   0.0667   1.0000
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