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GOE 528 AIRFOIL (goe528-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 528 AIRFOIL (goe528-il)
Reynolds number: 100,000
Max Cl/Cd: 55.67 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe528-il-100000-n5.txt
Download as CSV file: xf-goe528-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 528 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1729   0.10994   0.10518  -0.0540   0.9759   0.0587
  -9.500  -0.1702   0.10708   0.10234  -0.0619   0.9640   0.0606
  -9.250  -0.1569   0.10265   0.09793  -0.0653   0.9555   0.0614
  -9.000  -0.1306   0.09866   0.09390  -0.0653   0.9505   0.0636
  -8.750  -0.1133   0.09517   0.09040  -0.0687   0.9422   0.0656
  -8.500  -0.0962   0.09142   0.08662  -0.0739   0.9348   0.0683
  -8.250  -0.0916   0.08818   0.08339  -0.0833   0.9209   0.0709
  -8.000  -0.0849   0.08439   0.07957  -0.0914   0.9070   0.0713
  -7.750  -0.0591   0.07991   0.07507  -0.0897   0.9034   0.0729
  -7.500  -0.0373   0.07702   0.07215  -0.0902   0.8955   0.0755
  -7.250  -0.0228   0.07388   0.06896  -0.0935   0.8853   0.0778
  -6.750  -0.0170   0.05883   0.05356  -0.1124   0.8576   0.0519
  -6.500  -0.0016   0.05389   0.04841  -0.1168   0.8486   0.0520
  -6.250   0.0111   0.05022   0.04459  -0.1185   0.8379   0.0519
  -6.000   0.0281   0.04721   0.04144  -0.1196   0.8292   0.0515
  -5.750   0.0444   0.04388   0.03791  -0.1208   0.8197   0.0511
  -5.500   0.0613   0.04038   0.03412  -0.1219   0.8106   0.0507
  -5.250   0.0794   0.03617   0.02932  -0.1232   0.8019   0.0515
  -5.000   0.0984   0.03324   0.02587  -0.1232   0.7929   0.0520
  -4.750   0.1210   0.03098   0.02325  -0.1232   0.7847   0.0522
  -4.500   0.1427   0.02916   0.02112  -0.1227   0.7756   0.0524
  -4.250   0.1675   0.02754   0.01920  -0.1224   0.7675   0.0529
  -4.000   0.1907   0.02644   0.01792  -0.1218   0.7581   0.0539
  -3.750   0.2170   0.02544   0.01670  -0.1216   0.7501   0.0555
  -3.500   0.2409   0.02444   0.01544  -0.1209   0.7405   0.0569
  -3.250   0.2683   0.02331   0.01399  -0.1205   0.7327   0.0577
  -3.000   0.2927   0.02243   0.01288  -0.1197   0.7229   0.0586
  -2.750   0.3208   0.02158   0.01176  -0.1194   0.7154   0.0596
  -2.500   0.3452   0.02100   0.01099  -0.1185   0.7052   0.0609
  -2.250   0.3722   0.02036   0.01035  -0.1183   0.6975   0.0633
  -2.000   0.3965   0.01996   0.00991  -0.1175   0.6876   0.0660
  -1.750   0.4233   0.01948   0.00932  -0.1170   0.6797   0.0683
  -1.500   0.4480   0.01912   0.00888  -0.1162   0.6703   0.0707
  -1.250   0.4738   0.01872   0.00843  -0.1156   0.6625   0.0739
  -1.000   0.4986   0.01847   0.00816  -0.1149   0.6535   0.0796
  -0.750   0.5247   0.01820   0.00784  -0.1143   0.6457   0.0884
  -0.500   0.5499   0.01796   0.00759  -0.1137   0.6372   0.1027
  -0.250   0.5768   0.01759   0.00734  -0.1134   0.6299   0.1460
   0.000   0.6019   0.01710   0.00738  -0.1131   0.6215   0.3102
   0.500   0.6765   0.01572   0.00734  -0.1164   0.6059   1.0000
   0.750   0.7032   0.01587   0.00724  -0.1160   0.5996   1.0000
   1.000   0.7267   0.01609   0.00735  -0.1151   0.5914   1.0000
   1.250   0.7528   0.01627   0.00733  -0.1146   0.5848   1.0000
   1.500   0.7769   0.01650   0.00745  -0.1139   0.5774   1.0000
   1.750   0.8020   0.01671   0.00752  -0.1133   0.5706   1.0000
   2.000   0.8274   0.01693   0.00762  -0.1127   0.5641   1.0000
   2.250   0.8513   0.01718   0.00779  -0.1119   0.5568   1.0000
   2.500   0.8777   0.01740   0.00786  -0.1116   0.5511   1.0000
   2.750   0.9006   0.01769   0.00812  -0.1107   0.5438   1.0000
   3.000   0.9255   0.01794   0.00828  -0.1101   0.5373   1.0000
   3.250   0.9504   0.01821   0.00847  -0.1096   0.5312   1.0000
   3.500   0.9733   0.01851   0.00875  -0.1087   0.5239   1.0000
   3.750   0.9991   0.01876   0.00890  -0.1083   0.5181   1.0000
   4.000   1.0211   0.01909   0.00924  -0.1073   0.5110   1.0000
   4.250   1.0449   0.01938   0.00950  -0.1066   0.5043   1.0000
   4.500   1.0691   0.01967   0.00974  -0.1059   0.4981   1.0000
   4.750   1.0904   0.02002   0.01012  -0.1049   0.4907   1.0000
   5.000   1.1153   0.02029   0.01032  -0.1043   0.4846   1.0000
   5.250   1.1353   0.02066   0.01076  -0.1031   0.4771   1.0000
   5.500   1.1580   0.02097   0.01105  -0.1023   0.4704   1.0000
   5.750   1.1798   0.02132   0.01140  -0.1013   0.4637   1.0000
   6.000   1.1999   0.02168   0.01183  -0.1001   0.4562   1.0000
   6.250   1.2236   0.02198   0.01207  -0.0994   0.4503   1.0000
   6.500   1.2407   0.02242   0.01262  -0.0978   0.4424   1.0000
   6.750   1.2626   0.02274   0.01295  -0.0968   0.4360   1.0000
   7.000   1.2805   0.02319   0.01347  -0.0953   0.4288   1.0000
   7.250   1.2997   0.02358   0.01391  -0.0940   0.4220   1.0000
   7.500   1.3192   0.02399   0.01436  -0.0928   0.4157   1.0000
   7.750   1.3354   0.02448   0.01494  -0.0911   0.4084   1.0000
   8.000   1.3565   0.02483   0.01526  -0.0901   0.4026   1.0000
   8.250   1.3688   0.02544   0.01601  -0.0879   0.3949   1.0000
   8.500   1.3861   0.02587   0.01648  -0.0863   0.3886   1.0000
   8.750   1.3987   0.02644   0.01714  -0.0841   0.3819   1.0000
   9.000   1.4113   0.02700   0.01777  -0.0819   0.3751   1.0000
   9.250   1.4256   0.02754   0.01834  -0.0801   0.3687   1.0000
   9.500   1.4346   0.02827   0.01919  -0.0776   0.3613   1.0000
   9.750   1.4492   0.02879   0.01970  -0.0758   0.3548   1.0000
  10.000   1.4540   0.02972   0.02077  -0.0730   0.3467   1.0000
  10.250   1.4672   0.03031   0.02133  -0.0713   0.3398   1.0000
  10.500   1.4701   0.03145   0.02264  -0.0686   0.3319   1.0000
  10.750   1.4810   0.03222   0.02343  -0.0668   0.3250   1.0000
  11.000   1.4849   0.03348   0.02483  -0.0646   0.3180   1.0000
  11.250   1.4933   0.03453   0.02596  -0.0628   0.3118   1.0000
  11.500   1.5013   0.03567   0.02718  -0.0611   0.3059   1.0000
  11.750   1.5048   0.03714   0.02880  -0.0593   0.2995   1.0000
  12.000   1.5153   0.03815   0.02983  -0.0579   0.2938   1.0000
  12.250   1.5144   0.04006   0.03193  -0.0560   0.2873   1.0000
  12.500   1.5180   0.04161   0.03355  -0.0545   0.2806   1.0000
  12.750   1.5184   0.04353   0.03559  -0.0530   0.2739   1.0000
  13.000   1.5175   0.04563   0.03781  -0.0517   0.2672   1.0000
  13.250   1.5218   0.04735   0.03960  -0.0506   0.2615   1.0000
  13.500   1.5165   0.05011   0.04255  -0.0495   0.2551   1.0000
  13.750   1.5194   0.05200   0.04447  -0.0485   0.2488   1.0000
  14.000   1.5095   0.05546   0.04812  -0.0478   0.2417   1.0000
  14.250   1.5077   0.05803   0.05076  -0.0472   0.2350   1.0000
  14.500   1.4996   0.06160   0.05450  -0.0469   0.2284   1.0000
  14.750   1.4938   0.06495   0.05795  -0.0467   0.2215   1.0000
  15.000   1.4856   0.06878   0.06192  -0.0468   0.2147   1.0000
  15.250   1.4765   0.07284   0.06611  -0.0472   0.2073   1.0000
  15.500   1.4656   0.07732   0.07072  -0.0477   0.1999   1.0000
  15.750   1.4561   0.08168   0.07516  -0.0484   0.1917   1.0000
  16.000   1.4392   0.08739   0.08103  -0.0497   0.1834   1.0000
  16.250   1.4285   0.09214   0.08581  -0.0508   0.1740   1.0000
  16.500   1.4115   0.09815   0.09194  -0.0525   0.1643   1.0000
  16.750   1.3951   0.10422   0.09810  -0.0544   0.1540   1.0000
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