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GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 598 AIRFOIL (goe598-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.51 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe598-il-1000000.txt
Download as CSV file: xf-goe598-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 598 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.6526   0.13304   0.13142   0.0270   1.0000   0.0067
 -11.000  -0.6484   0.12947   0.12785   0.0256   1.0000   0.0070
  -7.000  -0.6411   0.01990   0.01610  -0.0293   1.0000   0.0064
  -6.750  -0.6208   0.01673   0.01246  -0.0285   1.0000   0.0066
  -6.500  -0.5965   0.01560   0.01116  -0.0281   1.0000   0.0070
  -6.250  -0.5713   0.01492   0.01037  -0.0278   1.0000   0.0077
  -6.000  -0.5465   0.01404   0.00936  -0.0273   1.0000   0.0083
  -5.750  -0.5219   0.01305   0.00822  -0.0268   1.0000   0.0089
  -5.500  -0.4973   0.01226   0.00731  -0.0262   1.0000   0.0093
  -5.250  -0.4724   0.01179   0.00677  -0.0256   1.0000   0.0097
  -5.000  -0.4500   0.01015   0.00494  -0.0247   1.0000   0.0115
  -4.750  -0.4248   0.01000   0.00479  -0.0242   1.0000   0.0128
  -4.500  -0.4002   0.00967   0.00443  -0.0236   1.0000   0.0142
  -4.250  -0.3755   0.00947   0.00420  -0.0229   1.0000   0.0152
  -4.000  -0.3517   0.00862   0.00326  -0.0222   1.0000   0.0180
  -3.750  -0.3259   0.00843   0.00307  -0.0219   0.9998   0.0208
  -3.500  -0.2909   0.00825   0.00289  -0.0236   0.9977   0.0236
  -3.250  -0.2561   0.00794   0.00253  -0.0253   0.9956   0.0256
  -3.000  -0.2215   0.00747   0.00200  -0.0268   0.9935   0.0304
  -2.750  -0.1876   0.00722   0.00169  -0.0283   0.9901   0.0339
  -2.500  -0.1529   0.00704   0.00147  -0.0298   0.9864   0.0358
  -2.250  -0.1176   0.00688   0.00131  -0.0315   0.9824   0.0386
  -2.000  -0.0869   0.00673   0.00119  -0.0321   0.9729   0.0458
  -1.750  -0.0571   0.00654   0.00110  -0.0325   0.9608   0.0757
  -1.500  -0.0300   0.00642   0.00101  -0.0322   0.9444   0.0904
  -1.250  -0.0044   0.00624   0.00091  -0.0316   0.9240   0.1225
  -1.000   0.0204   0.00588   0.00081  -0.0310   0.8988   0.2232
  -0.750   0.0453   0.00544   0.00072  -0.0305   0.8714   0.3577
  -0.500   0.0702   0.00504   0.00067  -0.0301   0.8401   0.5068
  -0.250   0.0961   0.00489   0.00066  -0.0297   0.8095   0.5894
   0.000   0.1226   0.00475   0.00066  -0.0294   0.7870   0.6576
   0.250   0.1489   0.00456   0.00068  -0.0291   0.7667   0.7380
   0.500   0.1733   0.00432   0.00072  -0.0282   0.7462   0.8383
   0.750   0.1939   0.00416   0.00076  -0.0261   0.7197   0.9419
   1.000   0.2367   0.00421   0.00076  -0.0294   0.6934   1.0000
   1.250   0.2638   0.00430   0.00078  -0.0292   0.6739   1.0000
   1.500   0.2909   0.00440   0.00083  -0.0291   0.6544   1.0000
   1.750   0.3177   0.00456   0.00087  -0.0289   0.6223   1.0000
   2.000   0.3444   0.00475   0.00092  -0.0287   0.5777   1.0000
   2.250   0.3691   0.00539   0.00102  -0.0283   0.4316   1.0000
   2.500   0.3940   0.00609   0.00125  -0.0281   0.3063   1.0000
   2.750   0.4192   0.00678   0.00147  -0.0280   0.1843   1.0000
   3.000   0.4452   0.00730   0.00171  -0.0279   0.1114   1.0000
   3.250   0.4704   0.00805   0.00206  -0.0276   0.0223   1.0000
   3.500   0.4975   0.00834   0.00238  -0.0274   0.0170   1.0000
   3.750   0.5244   0.00868   0.00276  -0.0272   0.0145   1.0000
   4.000   0.5499   0.00949   0.00372  -0.0267   0.0116   1.0000
   4.250   0.5767   0.00979   0.00404  -0.0265   0.0111   1.0000
   4.500   0.6029   0.01028   0.00458  -0.0262   0.0104   1.0000
   4.750   0.6288   0.01085   0.00521  -0.0258   0.0096   1.0000
   5.000   0.6545   0.01144   0.00586  -0.0255   0.0087   1.0000
   5.250   0.6796   0.01221   0.00668  -0.0250   0.0080   1.0000
   5.500   0.7035   0.01344   0.00801  -0.0242   0.0077   1.0000
   5.750   0.7276   0.01492   0.00963  -0.0234   0.0078   1.0000
   6.000   0.7513   0.01656   0.01141  -0.0227   0.0075   1.0000
   6.250   0.7736   0.01904   0.01414  -0.0217   0.0073   1.0000
   6.500   0.7971   0.02074   0.01605  -0.0210   0.0073   1.0000
   6.750   0.8197   0.02277   0.01837  -0.0200   0.0075   1.0000
  12.500   0.7972   0.15506   0.15347  -0.0605   0.0068   1.0000
  12.750   0.8007   0.15962   0.15803  -0.0623   0.0068   1.0000
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