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GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 602 AIRFOIL (goe602-il)
Reynolds number: 200,000
Max Cl/Cd: 73.96 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe602-il-200000-n5.txt
Download as CSV file: xf-goe602-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3952   0.08772   0.08440  -0.0374   1.0000   0.0156
  -8.500  -0.4074   0.08465   0.08141  -0.0365   1.0000   0.0155
  -8.250  -0.4240   0.08180   0.07863  -0.0350   1.0000   0.0153
  -8.000  -0.4243   0.07615   0.07303  -0.0407   0.9952   0.0153
  -7.750  -0.4141   0.06660   0.06347  -0.0540   0.9871   0.0150
  -7.500  -0.4075   0.05168   0.04831  -0.0706   0.9775   0.0147
  -7.250  -0.4014   0.04075   0.03685  -0.0776   0.9688   0.0148
  -7.000  -0.3835   0.03447   0.03003  -0.0810   0.9638   0.0153
  -6.750  -0.3643   0.03079   0.02588  -0.0819   0.9576   0.0165
  -6.500  -0.3378   0.02710   0.02155  -0.0835   0.9542   0.0185
  -6.250  -0.3133   0.02430   0.01812  -0.0837   0.9495   0.0199
  -6.000  -0.2890   0.02204   0.01553  -0.0839   0.9446   0.0213
  -5.750  -0.2573   0.02129   0.01464  -0.0852   0.9416   0.0234
  -5.500  -0.2235   0.02024   0.01334  -0.0867   0.9394   0.0265
  -5.250  -0.1969   0.01920   0.01201  -0.0864   0.9341   0.0288
  -5.000  -0.1678   0.01795   0.01057  -0.0870   0.9298   0.0316
  -4.750  -0.1345   0.01709   0.00962  -0.0883   0.9269   0.0347
  -4.500  -0.0996   0.01639   0.00879  -0.0898   0.9244   0.0383
  -4.250  -0.0749   0.01583   0.00811  -0.0891   0.9172   0.0403
  -4.000  -0.0431   0.01505   0.00724  -0.0899   0.9129   0.0422
  -3.750  -0.0107   0.01429   0.00645  -0.0910   0.9089   0.0458
  -3.500   0.0151   0.01383   0.00593  -0.0905   0.9011   0.0479
  -3.250   0.0486   0.01335   0.00536  -0.0916   0.8964   0.0506
  -3.000   0.0752   0.01303   0.00494  -0.0913   0.8882   0.0532
  -2.750   0.1071   0.01261   0.00449  -0.0920   0.8823   0.0585
  -2.500   0.1338   0.01232   0.00420  -0.0917   0.8738   0.0688
  -2.250   0.1647   0.01186   0.00388  -0.0924   0.8674   0.1120
  -2.000   0.1896   0.01142   0.00366  -0.0919   0.8578   0.1754
  -1.750   0.2171   0.01094   0.00352  -0.0920   0.8495   0.2859
  -1.500   0.2444   0.01060   0.00336  -0.0920   0.8404   0.3579
  -1.250   0.2691   0.01021   0.00328  -0.0914   0.8299   0.4505
  -1.000   0.2929   0.00975   0.00324  -0.0904   0.8197   0.5768
  -0.750   0.3166   0.00935   0.00319  -0.0892   0.8092   0.7019
  -0.500   0.3468   0.00894   0.00323  -0.0887   0.7982   0.8724
  -0.250   0.4128   0.00881   0.00308  -0.0964   0.7875   0.9812
   0.000   0.4526   0.00882   0.00296  -0.0990   0.7744   1.0000
   0.250   0.4775   0.00885   0.00287  -0.0983   0.7596   1.0000
   0.500   0.5023   0.00891   0.00281  -0.0976   0.7445   1.0000
   0.750   0.5269   0.00899   0.00278  -0.0968   0.7290   1.0000
   1.000   0.5514   0.00909   0.00276  -0.0961   0.7131   1.0000
   1.250   0.5758   0.00921   0.00277  -0.0952   0.6966   1.0000
   1.500   0.5999   0.00934   0.00279  -0.0944   0.6800   1.0000
   1.750   0.6233   0.00949   0.00283  -0.0934   0.6603   1.0000
   2.000   0.6466   0.00966   0.00289  -0.0924   0.6398   1.0000
   2.250   0.6694   0.00985   0.00296  -0.0913   0.6170   1.0000
   2.500   0.6923   0.01005   0.00305  -0.0902   0.5964   1.0000
   2.750   0.7153   0.01026   0.00318  -0.0892   0.5770   1.0000
   3.000   0.7386   0.01046   0.00331  -0.0883   0.5592   1.0000
   3.250   0.7620   0.01067   0.00346  -0.0874   0.5423   1.0000
   3.500   0.7852   0.01089   0.00363  -0.0865   0.5253   1.0000
   3.750   0.8082   0.01113   0.00383  -0.0855   0.5084   1.0000
   4.250   0.8533   0.01165   0.00425  -0.0835   0.4708   1.0000
   4.500   0.8760   0.01192   0.00450  -0.0826   0.4535   1.0000
   4.750   0.8988   0.01219   0.00476  -0.0816   0.4377   1.0000
   5.000   0.9216   0.01246   0.00504  -0.0807   0.4227   1.0000
   5.250   0.9435   0.01278   0.00533  -0.0796   0.4044   1.0000
   5.500   0.9624   0.01321   0.00565  -0.0780   0.3702   1.0000
   5.750   0.9787   0.01378   0.00600  -0.0761   0.3215   1.0000
   6.000   0.9950   0.01442   0.00642  -0.0742   0.2750   1.0000
   6.250   1.0087   0.01529   0.00696  -0.0720   0.2174   1.0000
   6.500   1.0227   0.01621   0.00759  -0.0699   0.1611   1.0000
   6.750   1.0320   0.01752   0.00848  -0.0672   0.0961   1.0000
   7.250   1.0551   0.01976   0.01034  -0.0622   0.0267   1.0000
   7.500   1.0709   0.02045   0.01117  -0.0602   0.0228   1.0000
   7.750   1.0838   0.02127   0.01210  -0.0578   0.0199   1.0000
   8.000   1.0945   0.02226   0.01323  -0.0551   0.0181   1.0000
   8.250   1.1032   0.02334   0.01446  -0.0522   0.0169   1.0000
   8.500   1.1153   0.02419   0.01543  -0.0499   0.0160   1.0000
   8.750   1.1257   0.02516   0.01656  -0.0475   0.0149   1.0000
   9.000   1.1344   0.02626   0.01777  -0.0450   0.0140   1.0000
   9.250   1.1409   0.02753   0.01915  -0.0423   0.0133   1.0000
   9.500   1.1468   0.02891   0.02062  -0.0398   0.0129   1.0000
   9.750   1.1516   0.03043   0.02223  -0.0373   0.0124   1.0000
  10.000   1.1559   0.03209   0.02397  -0.0350   0.0120   1.0000
  10.250   1.1590   0.03402   0.02596  -0.0327   0.0115   1.0000
  10.500   1.1620   0.03643   0.02842  -0.0306   0.0110   1.0000
  10.750   1.1715   0.03794   0.03006  -0.0291   0.0105   1.0000
  11.000   1.1806   0.03948   0.03174  -0.0277   0.0100   1.0000
  11.250   1.1899   0.04137   0.03375  -0.0263   0.0097   1.0000
  11.500   1.1991   0.04337   0.03593  -0.0249   0.0094   1.0000
  11.750   1.2071   0.04550   0.03822  -0.0237   0.0092   1.0000
  12.000   1.2139   0.04782   0.04072  -0.0224   0.0090   1.0000
  12.250   1.2188   0.05029   0.04337  -0.0213   0.0088   1.0000
  12.500   1.2214   0.05298   0.04625  -0.0203   0.0086   1.0000
  12.750   1.2220   0.05589   0.04936  -0.0194   0.0085   1.0000
  13.000   1.2203   0.05905   0.05273  -0.0187   0.0084   1.0000
  13.250   1.2164   0.06251   0.05640  -0.0183   0.0083   1.0000
  13.500   1.2110   0.06616   0.06025  -0.0183   0.0083   1.0000
  13.750   1.2047   0.06998   0.06424  -0.0186   0.0081   1.0000
  14.000   1.1959   0.07429   0.06876  -0.0193   0.0081   1.0000
  14.250   1.1855   0.07897   0.07364  -0.0205   0.0080   1.0000
  14.500   1.1772   0.08334   0.07814  -0.0221   0.0078   1.0000
  14.750   1.1668   0.08840   0.08335  -0.0241   0.0077   1.0000
  15.000   1.1526   0.09454   0.08971  -0.0268   0.0077   1.0000
  15.250   1.1404   0.10047   0.09581  -0.0298   0.0077   1.0000
  15.500   1.1267   0.10704   0.10255  -0.0333   0.0077   1.0000
  15.750   1.1124   0.11410   0.10979  -0.0373   0.0076   1.0000
  16.000   1.0974   0.12171   0.11758  -0.0419   0.0076   1.0000
  16.250   1.0818   0.12993   0.12597  -0.0471   0.0077   1.0000
  16.500   1.0393   0.14713   0.14356  -0.0584   0.0083   1.0000
  16.750   1.0110   0.16192   0.15851  -0.0676   0.0086   1.0000
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