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GOE 480 AIRFOIL (goe480-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 480 AIRFOIL (goe480-il)
Reynolds number: 100,000
Max Cl/Cd: 52.14 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe480-il-100000.txt
Download as CSV file: xf-goe480-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 480 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3174   0.10974   0.10513  -0.0251   1.0000   0.1071
  -8.250  -0.3345   0.10940   0.10488  -0.0227   1.0000   0.1092
  -8.000  -0.3561   0.10978   0.10530  -0.0364   0.9870   0.1125
  -7.750  -0.3148   0.10237   0.09785  -0.0345   0.9868   0.1147
  -7.500  -0.2838   0.09834   0.09378  -0.0370   0.9830   0.1183
  -7.250  -0.2705   0.09548   0.09091  -0.0412   0.9745   0.1231
  -7.000  -0.2775   0.09265   0.08806  -0.0574   0.9581   0.1280
  -6.750  -0.2466   0.08848   0.08391  -0.0523   0.9572   0.1306
  -6.500  -0.2258   0.08555   0.08096  -0.0537   0.9503   0.1350
  -6.250  -0.2205   0.08229   0.07755  -0.0711   0.9348   0.1436
  -6.000  -0.1994   0.07845   0.07378  -0.0671   0.9301   0.1453
  -5.750  -0.1705   0.07537   0.07068  -0.0677   0.9259   0.1498
  -5.500  -0.1604   0.07235   0.06748  -0.0788   0.9128   0.1604
  -5.250  -0.1325   0.06893   0.06413  -0.0770   0.9095   0.1635
  -5.000  -0.1141   0.06668   0.06185  -0.0778   0.9018   0.1694
  -4.750  -0.0903   0.06307   0.05809  -0.0848   0.8934   0.1789
  -4.500  -0.0648   0.06159   0.05637  -0.0898   0.8847   0.1925
  -4.250  -0.0457   0.05791   0.05276  -0.0895   0.8781   0.1958
  -4.000  -0.0046   0.05484   0.04953  -0.0955   0.8744   0.2118
  -3.750   0.0021   0.05325   0.04802  -0.0921   0.8640   0.2151
  -3.500   0.0393   0.05042   0.04505  -0.0966   0.8593   0.2308
  -3.250   0.0813   0.04759   0.04210  -0.1009   0.8563   0.2481
  -3.000   0.0891   0.04677   0.04119  -0.0992   0.8441   0.2639
  -2.750   0.1255   0.04426   0.03866  -0.1012   0.8406   0.2832
  -2.500   0.1719   0.03762   0.03031  -0.1090   0.8303   0.1599
  -2.250   0.2099   0.03394   0.02625  -0.1108   0.8255   0.1406
  -2.000   0.2524   0.03145   0.02345  -0.1131   0.8222   0.1352
  -1.750   0.2666   0.03081   0.02258  -0.1109   0.8109   0.1345
  -1.500   0.3074   0.02920   0.02067  -0.1125   0.8066   0.1344
  -1.250   0.3299   0.02848   0.01971  -0.1114   0.7977   0.1333
  -1.000   0.3639   0.02743   0.01843  -0.1118   0.7913   0.1333
  -0.750   0.4057   0.02622   0.01705  -0.1134   0.7874   0.1348
  -0.500   0.4214   0.02620   0.01698  -0.1112   0.7760   0.1368
  -0.250   0.4606   0.02537   0.01599  -0.1123   0.7712   0.1419
   0.000   0.4797   0.02521   0.01586  -0.1106   0.7610   0.1453
   0.250   0.5144   0.02448   0.01519  -0.1111   0.7551   0.1507
   0.500   0.5385   0.02432   0.01503  -0.1101   0.7464   0.1572
   0.750   0.5679   0.02384   0.01464  -0.1097   0.7388   0.1683
   1.000   0.6069   0.02302   0.01389  -0.1107   0.7345   0.1961
   1.250   0.6580   0.02081   0.01378  -0.1154   0.7239   1.0000
   1.500   0.6934   0.02060   0.01328  -0.1157   0.7182   1.0000
   1.750   0.7098   0.02112   0.01371  -0.1137   0.7070   1.0000
   2.000   0.7444   0.02091   0.01332  -0.1140   0.7010   1.0000
   2.250   0.7612   0.02142   0.01378  -0.1120   0.6898   1.0000
   2.500   0.7957   0.02120   0.01340  -0.1124   0.6837   1.0000
   2.750   0.8125   0.02170   0.01388  -0.1104   0.6725   1.0000
   3.000   0.8476   0.02143   0.01347  -0.1108   0.6662   1.0000
   3.250   0.8640   0.02193   0.01397  -0.1088   0.6548   1.0000
   3.500   0.9001   0.02161   0.01351  -0.1094   0.6487   1.0000
   3.750   0.9156   0.02213   0.01406  -0.1072   0.6370   1.0000
   4.000   0.9472   0.02200   0.01385  -0.1072   0.6297   1.0000
   4.250   0.9677   0.02229   0.01414  -0.1057   0.6191   1.0000
   4.500   0.9929   0.02244   0.01426  -0.1049   0.6101   1.0000
   4.750   1.0203   0.02246   0.01424  -0.1044   0.6011   1.0000
   5.000   1.0413   0.02279   0.01459  -0.1030   0.5910   1.0000
   5.250   1.0734   0.02265   0.01436  -0.1031   0.5830   1.0000
   5.500   1.0914   0.02311   0.01489  -0.1013   0.5719   1.0000
   5.750   1.1243   0.02300   0.01468  -0.1016   0.5640   1.0000
   6.000   1.1426   0.02344   0.01519  -0.0999   0.5528   1.0000
   6.250   1.1661   0.02374   0.01551  -0.0989   0.5429   1.0000
   6.500   1.1951   0.02380   0.01552  -0.0987   0.5335   1.0000
   6.750   1.2126   0.02437   0.01616  -0.0969   0.5224   1.0000
   7.000   1.2428   0.02449   0.01623  -0.0969   0.5134   1.0000
   7.250   1.2614   0.02497   0.01679  -0.0953   0.5023   1.0000
   7.500   1.2820   0.02548   0.01735  -0.0940   0.4919   1.0000
   7.750   1.3130   0.02561   0.01740  -0.0941   0.4825   1.0000
   8.000   1.3264   0.02623   0.01816  -0.0917   0.4705   1.0000
   8.250   1.3475   0.02655   0.01849  -0.0904   0.4589   1.0000
   8.500   1.3746   0.02659   0.01843  -0.0899   0.4471   1.0000
   8.750   1.3910   0.02694   0.01886  -0.0878   0.4348   1.0000
   9.000   1.4054   0.02740   0.01941  -0.0856   0.4228   1.0000
   9.250   1.4252   0.02767   0.01967  -0.0841   0.4110   1.0000
   9.500   1.4475   0.02776   0.01969  -0.0829   0.3986   1.0000
   9.750   1.4565   0.02817   0.02021  -0.0798   0.3858   1.0000
  10.000   1.4653   0.02864   0.02076  -0.0767   0.3735   1.0000
  10.250   1.4774   0.02903   0.02118  -0.0742   0.3617   1.0000
  10.500   1.4910   0.02933   0.02146  -0.0718   0.3497   1.0000
  10.750   1.4901   0.02996   0.02223  -0.0675   0.3383   1.0000
  11.000   1.4906   0.03062   0.02297  -0.0634   0.3269   1.0000
  11.250   1.4922   0.03128   0.02365  -0.0598   0.3147   1.0000
  11.500   1.4922   0.03206   0.02444  -0.0562   0.3019   1.0000
  11.750   1.4856   0.03325   0.02573  -0.0522   0.2884   1.0000
  12.000   1.4775   0.03471   0.02727  -0.0486   0.2737   1.0000
  12.250   1.4676   0.03650   0.02908  -0.0454   0.2569   1.0000
  12.500   1.4541   0.03885   0.03148  -0.0424   0.2376   1.0000
  12.750   1.4371   0.04184   0.03446  -0.0399   0.2149   1.0000
  13.000   1.4180   0.04543   0.03794  -0.0378   0.1909   1.0000
  13.250   1.3991   0.04940   0.04176  -0.0363   0.1689   1.0000
  13.500   1.3825   0.05346   0.04565  -0.0351   0.1515   1.0000
  13.750   1.3700   0.05736   0.04942  -0.0343   0.1378   1.0000
  14.000   1.3611   0.06102   0.05298  -0.0337   0.1270   1.0000
  14.250   1.3570   0.06429   0.05624  -0.0331   0.1177   1.0000
  14.500   1.3561   0.06717   0.05903  -0.0324   0.1100   1.0000
  14.750   1.3580   0.06976   0.06155  -0.0317   0.1033   1.0000
  15.000   1.3648   0.07189   0.06369  -0.0308   0.0973   1.0000
  15.250   1.3750   0.07360   0.06531  -0.0299   0.0919   1.0000
  15.500   1.3871   0.07532   0.06706  -0.0289   0.0872   1.0000
  15.750   1.3955   0.07751   0.06932  -0.0283   0.0832   1.0000
  16.000   1.4270   0.07757   0.06918  -0.0265   0.0785   1.0000
  16.250   1.4255   0.08096   0.07286  -0.0264   0.0764   1.0000
  16.500   1.4265   0.08417   0.07626  -0.0264   0.0740   1.0000
  16.750   1.4372   0.08641   0.07855  -0.0260   0.0715   1.0000
  17.000   1.4652   0.08791   0.08000  -0.0248   0.0687   1.0000
  17.250   1.4515   0.09258   0.08498  -0.0256   0.0680   1.0000
  17.500   1.4358   0.09772   0.09042  -0.0269   0.0673   1.0000
  17.750   1.4188   0.10329   0.09629  -0.0286   0.0668   1.0000
  18.000   1.3995   0.10941   0.10269  -0.0309   0.0663   1.0000
  18.250   1.3774   0.11629   0.10984  -0.0339   0.0662   1.0000
  18.500   1.3503   0.12431   0.11814  -0.0380   0.0662   1.0000
  18.750   1.3174   0.13390   0.12801  -0.0435   0.0666   1.0000
  19.000   1.2796   0.14532   0.13968  -0.0505   0.0675   1.0000
  19.250   1.2376   0.15876   0.15332  -0.0591   0.0685   1.0000
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