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GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 393 AIRFOIL (goe393-il)
Reynolds number: 200,000
Max Cl/Cd: 75.36 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe393-il-200000.txt
Download as CSV file: xf-goe393-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 393 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4780   0.11111   0.10767   0.0187   1.0000   0.0390
  -8.500  -0.4765   0.10937   0.10597   0.0134   1.0000   0.0403
  -8.250  -0.4765   0.10739   0.10406   0.0076   1.0000   0.0406
  -8.000  -0.4673   0.10405   0.10073   0.0011   1.0000   0.0408
  -7.750  -0.4606   0.09768   0.09439   0.0071   1.0000   0.0416
  -7.500  -0.4498   0.09403   0.09074   0.0082   1.0000   0.0425
  -7.250  -0.4399   0.09086   0.08759   0.0069   1.0000   0.0437
  -7.000  -0.4285   0.08758   0.08432   0.0043   1.0000   0.0452
  -6.750  -0.4149   0.08412   0.08088   0.0003   1.0000   0.0476
  -6.500  -0.3757   0.08087   0.07747  -0.0204   1.0000   0.0506
  -6.250  -0.3739   0.07525   0.07195  -0.0165   1.0000   0.0514
  -6.000  -0.3628   0.07198   0.06871  -0.0148   1.0000   0.0525
  -5.750  -0.3465   0.06891   0.06565  -0.0160   1.0000   0.0541
  -5.500  -0.3259   0.06563   0.06234  -0.0191   1.0000   0.0568
  -5.000  -0.2690   0.05725   0.05377  -0.0313   1.0000   0.0629
  -4.750  -0.2525   0.05453   0.05108  -0.0311   1.0000   0.0645
  -4.500  -0.2301   0.05176   0.04830  -0.0327   1.0000   0.0671
  -4.250  -0.1773   0.04938   0.04537  -0.0417   1.0000   0.0735
  -4.000  -0.1663   0.04465   0.04085  -0.0413   0.9992   0.0747
  -3.750  -0.1261   0.04140   0.03760  -0.0458   0.9579   0.0776
  -3.500  -0.0723   0.03985   0.03546  -0.0514   0.8948   0.0862
  -3.250  -0.0488   0.03580   0.03107  -0.0519   0.8413   0.0874
  -2.750  -0.0076   0.03167   0.02658  -0.0506   0.7787   0.0907
  -2.500   0.0280   0.03189   0.02610  -0.0509   0.7586   0.1003
  -2.250   0.0572   0.02412   0.01773  -0.0520   0.7452   0.0746
  -2.000   0.0839   0.02207   0.01545  -0.0518   0.7301   0.0697
  -1.750   0.1129   0.01938   0.01225  -0.0517   0.7169   0.0669
  -1.500   0.1411   0.01791   0.01040  -0.0514   0.7040   0.0684
  -1.250   0.1694   0.01665   0.00878  -0.0511   0.6919   0.0704
  -1.000   0.1974   0.01557   0.00735  -0.0506   0.6809   0.0722
  -0.750   0.2250   0.01471   0.00630  -0.0502   0.6701   0.0754
  -0.500   0.2527   0.01441   0.00596  -0.0500   0.6589   0.0806
  -0.250   0.2803   0.01399   0.00543  -0.0496   0.6485   0.0897
   0.000   0.3076   0.01388   0.00525  -0.0492   0.6387   0.1064
   0.250   0.3351   0.01368   0.00502  -0.0490   0.6275   0.1238
   0.500   0.3624   0.01349   0.00480  -0.0487   0.6175   0.1344
   0.750   0.3896   0.01343   0.00466  -0.0484   0.6084   0.1450
   1.000   0.4171   0.01340   0.00465  -0.0482   0.5976   0.1579
   1.250   0.4442   0.01320   0.00452  -0.0480   0.5877   0.1669
   1.500   0.4714   0.01313   0.00436  -0.0476   0.5783   0.1711
   1.750   0.4986   0.01293   0.00425  -0.0473   0.5674   0.1760
   2.000   0.5259   0.01287   0.00422  -0.0470   0.5576   0.1828
   2.250   0.5529   0.01281   0.00417  -0.0467   0.5484   0.1927
   2.500   0.5803   0.01276   0.00421  -0.0465   0.5379   0.2071
   2.750   0.6073   0.01266   0.00427  -0.0462   0.5288   0.2536
   3.000   0.6384   0.01126   0.00426  -0.0466   0.5191   1.0000
   3.250   0.6657   0.01143   0.00436  -0.0462   0.5082   1.0000
   3.500   0.6927   0.01160   0.00445  -0.0459   0.4980   1.0000
   3.750   0.7196   0.01177   0.00452  -0.0455   0.4877   1.0000
   4.000   0.7466   0.01187   0.00463  -0.0452   0.4753   1.0000
   4.250   0.7735   0.01200   0.00474  -0.0448   0.4633   1.0000
   4.500   0.8003   0.01217   0.00489  -0.0445   0.4533   1.0000
   4.750   0.8271   0.01235   0.00505  -0.0442   0.4437   1.0000
   5.000   0.8540   0.01249   0.00525  -0.0439   0.4323   1.0000
   5.250   0.8807   0.01267   0.00545  -0.0436   0.4217   1.0000
   5.500   0.9073   0.01288   0.00566  -0.0432   0.4126   1.0000
   5.750   0.9341   0.01305   0.00592  -0.0429   0.4018   1.0000
   6.000   0.9606   0.01325   0.00619  -0.0426   0.3906   1.0000
   6.250   0.9869   0.01345   0.00644  -0.0422   0.3781   1.0000
   6.500   1.0127   0.01360   0.00666  -0.0418   0.3597   1.0000
   6.750   1.0380   0.01378   0.00685  -0.0413   0.3332   1.0000
   7.000   1.0626   0.01410   0.00710  -0.0409   0.2964   1.0000
   7.250   1.0861   0.01468   0.00749  -0.0404   0.2288   1.0000
   7.500   1.1059   0.01602   0.00840  -0.0399   0.1649   1.0000
   7.750   1.1270   0.01714   0.00939  -0.0394   0.1392   1.0000
   8.000   1.1492   0.01804   0.01028  -0.0389   0.1178   1.0000
   8.250   1.1700   0.01913   0.01130  -0.0383   0.0925   1.0000
   8.500   1.1878   0.02069   0.01270  -0.0374   0.0634   1.0000
   8.750   1.2050   0.02224   0.01419  -0.0364   0.0504   1.0000
   9.000   1.2240   0.02345   0.01550  -0.0354   0.0445   1.0000
   9.250   1.2372   0.02535   0.01737  -0.0340   0.0403   1.0000
   9.500   1.2549   0.02659   0.01876  -0.0329   0.0372   1.0000
   9.750   1.2701   0.02809   0.02032  -0.0317   0.0349   1.0000
  10.000   1.2826   0.03000   0.02226  -0.0302   0.0331   1.0000
  10.250   1.2941   0.03266   0.02500  -0.0285   0.0317   1.0000
  10.500   1.3096   0.03431   0.02686  -0.0272   0.0308   1.0000
  10.750   1.3234   0.03609   0.02882  -0.0259   0.0294   1.0000
  11.000   1.3358   0.03793   0.03081  -0.0246   0.0281   1.0000
  11.250   1.3462   0.04005   0.03309  -0.0232   0.0272   1.0000
  11.500   1.3542   0.04239   0.03560  -0.0217   0.0265   1.0000
  11.750   1.3596   0.04496   0.03836  -0.0201   0.0260   1.0000
  12.000   1.3621   0.04793   0.04152  -0.0186   0.0257   1.0000
  12.250   1.3603   0.05128   0.04509  -0.0173   0.0254   1.0000
  12.500   1.3545   0.05492   0.04898  -0.0164   0.0253   1.0000
  12.750   1.3455   0.05886   0.05318  -0.0162   0.0253   1.0000
  13.000   1.3338   0.06320   0.05778  -0.0169   0.0253   1.0000
  13.250   1.3201   0.06796   0.06279  -0.0183   0.0254   1.0000
  13.500   1.3042   0.07326   0.06833  -0.0204   0.0254   1.0000
  13.750   1.2853   0.07923   0.07455  -0.0234   0.0256   1.0000
  14.000   1.2607   0.08657   0.08218  -0.0276   0.0260   1.0000
  14.250   1.2211   0.09729   0.09326  -0.0346   0.0267   1.0000
  14.500   1.1742   0.11077   0.10703  -0.0439   0.0276   1.0000
  14.750   1.1258   0.12711   0.12360  -0.0549   0.0287   1.0000
  15.000   1.0707   0.14877   0.14535  -0.0682   0.0306   1.0000
  15.250   1.0531   0.15954   0.15607  -0.0732   0.0316   1.0000
  15.500   0.8552   0.14252   0.13928  -0.0465   0.0328   1.0000
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