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GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 442 AIRFOIL (goe442-il)
Reynolds number: 200,000
Max Cl/Cd: 73.41 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe442-il-200000.txt
Download as CSV file: xf-goe442-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 442 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3582   0.08829   0.08495  -0.0215   1.0000   0.0386
  -7.250  -0.3649   0.08636   0.08308  -0.0199   1.0000   0.0391
  -7.000  -0.3689   0.08407   0.08085  -0.0193   1.0000   0.0398
  -6.750  -0.3707   0.08153   0.07836  -0.0194   1.0000   0.0408
  -6.500  -0.3713   0.07888   0.07574  -0.0201   1.0000   0.0417
  -6.250  -0.3693   0.07597   0.07285  -0.0219   1.0000   0.0430
  -6.000  -0.3558   0.07237   0.06920  -0.0304   1.0000   0.0447
  -5.750  -0.3413   0.06848   0.06518  -0.0351   1.0000   0.0451
  -5.500  -0.3370   0.06295   0.05963  -0.0361   1.0000   0.0456
  -5.250  -0.3350   0.05998   0.05673  -0.0334   1.0000   0.0464
  -5.000  -0.3282   0.05765   0.05442  -0.0317   1.0000   0.0474
  -4.750  -0.3185   0.05538   0.05215  -0.0310   1.0000   0.0491
  -4.500  -0.2899   0.05172   0.04837  -0.0351   0.9979   0.0529
  -4.250  -0.2345   0.04385   0.03995  -0.0466   0.9933   0.0585
  -4.000  -0.2029   0.04085   0.03697  -0.0493   0.9882   0.0606
  -3.750  -0.1610   0.03746   0.03336  -0.0541   0.9841   0.0658
  -3.500  -0.1209   0.03278   0.02815  -0.0583   0.9778   0.0732
  -3.250  -0.0795   0.03022   0.02525  -0.0620   0.9728   0.0866
  -3.000  -0.0359   0.02385   0.01790  -0.0634   0.9696   0.0553
  -2.750   0.0021   0.02234   0.01583  -0.0646   0.9621   0.0573
  -2.500   0.0418   0.01904   0.01214  -0.0671   0.9584   0.0595
  -2.250   0.0781   0.01791   0.01092  -0.0685   0.9510   0.0650
  -2.000   0.1202   0.01693   0.00964  -0.0707   0.9452   0.0698
  -1.750   0.1590   0.01550   0.00816  -0.0726   0.9389   0.0767
  -1.500   0.1987   0.01465   0.00724  -0.0744   0.9314   0.0825
  -1.250   0.2410   0.01357   0.00619  -0.0769   0.9257   0.0893
  -1.000   0.2776   0.01286   0.00551  -0.0781   0.9160   0.0966
  -0.750   0.3117   0.01213   0.00487  -0.0788   0.9042   0.1068
  -0.500   0.3461   0.01153   0.00432  -0.0795   0.8906   0.1206
  -0.250   0.3788   0.01071   0.00393  -0.0800   0.8740   0.2160
   0.000   0.4443   0.00852   0.00365  -0.0874   0.8578   1.0000
   0.250   0.4773   0.00840   0.00331  -0.0877   0.8276   1.0000
   0.500   0.5074   0.00839   0.00306  -0.0875   0.7893   1.0000
   0.750   0.5344   0.00853   0.00290  -0.0866   0.7447   1.0000
   1.000   0.5585   0.00879   0.00283  -0.0853   0.6989   1.0000
   1.250   0.5814   0.00908   0.00284  -0.0839   0.6584   1.0000
   1.500   0.6042   0.00939   0.00288  -0.0826   0.6236   1.0000
   1.750   0.6274   0.00969   0.00296  -0.0814   0.5953   1.0000
   2.000   0.6509   0.01002   0.00307  -0.0803   0.5723   1.0000
   2.250   0.6750   0.01030   0.00321  -0.0794   0.5527   1.0000
   2.500   0.6992   0.01060   0.00337  -0.0785   0.5348   1.0000
   2.750   0.7235   0.01089   0.00356  -0.0777   0.5182   1.0000
   3.000   0.7478   0.01117   0.00374  -0.0768   0.5020   1.0000
   3.250   0.7722   0.01143   0.00392  -0.0760   0.4870   1.0000
   3.500   0.7968   0.01167   0.00411  -0.0753   0.4733   1.0000
   3.750   0.8213   0.01191   0.00433  -0.0745   0.4600   1.0000
   4.000   0.8458   0.01214   0.00453  -0.0738   0.4473   1.0000
   4.250   0.8703   0.01238   0.00473  -0.0730   0.4349   1.0000
   4.500   0.8945   0.01262   0.00493  -0.0722   0.4222   1.0000
   4.750   0.9187   0.01283   0.00517  -0.0714   0.4084   1.0000
   5.000   0.9425   0.01304   0.00539  -0.0706   0.3939   1.0000
   5.250   0.9660   0.01328   0.00562  -0.0696   0.3782   1.0000
   5.500   0.9893   0.01350   0.00586  -0.0687   0.3593   1.0000
   5.750   1.0116   0.01378   0.00612  -0.0676   0.3364   1.0000
   6.000   1.0330   0.01413   0.00641  -0.0664   0.3069   1.0000
   6.250   1.0531   0.01462   0.00678  -0.0650   0.2679   1.0000
   6.500   1.0720   0.01532   0.00726  -0.0635   0.2333   1.0000
   6.750   1.0922   0.01600   0.00784  -0.0622   0.2127   1.0000
   7.000   1.1127   0.01668   0.00845  -0.0609   0.2006   1.0000
   7.250   1.1331   0.01739   0.00909  -0.0597   0.1915   1.0000
   7.500   1.1550   0.01799   0.00975  -0.0587   0.1843   1.0000
   7.750   1.1763   0.01870   0.01047  -0.0576   0.1790   1.0000
   8.000   1.1982   0.01947   0.01126  -0.0567   0.1743   1.0000
   8.250   1.2192   0.02002   0.01188  -0.0557   0.1667   1.0000
   8.500   1.2388   0.02062   0.01252  -0.0545   0.1570   1.0000
   8.750   1.2574   0.02135   0.01322  -0.0533   0.1480   1.0000
   9.000   1.2775   0.02177   0.01382  -0.0521   0.1412   1.0000
   9.250   1.2959   0.02260   0.01463  -0.0509   0.1345   1.0000
   9.500   1.3146   0.02292   0.01517  -0.0495   0.1270   1.0000
   9.750   1.3312   0.02358   0.01589  -0.0480   0.1195   1.0000
  10.000   1.3474   0.02390   0.01638  -0.0464   0.1088   1.0000
  10.250   1.3672   0.02389   0.01654  -0.0452   0.0833   1.0000
  10.500   1.3715   0.02549   0.01778  -0.0420   0.0479   1.0000
  10.750   1.3698   0.02726   0.01954  -0.0380   0.0407   1.0000
  11.000   1.3722   0.02877   0.02119  -0.0346   0.0368   1.0000
  11.250   1.3716   0.03050   0.02300  -0.0313   0.0339   1.0000
  11.500   1.3638   0.03280   0.02537  -0.0277   0.0320   1.0000
  11.750   1.3653   0.03460   0.02734  -0.0252   0.0304   1.0000
  12.000   1.3651   0.03663   0.02954  -0.0231   0.0291   1.0000
  12.250   1.3638   0.03891   0.03195  -0.0212   0.0282   1.0000
  12.500   1.3615   0.04144   0.03459  -0.0197   0.0272   1.0000
  12.750   1.3583   0.04424   0.03747  -0.0185   0.0263   1.0000
  13.000   1.3553   0.04725   0.04057  -0.0176   0.0255   1.0000
  13.250   1.3530   0.05059   0.04398  -0.0165   0.0248   1.0000
  13.500   1.3517   0.05382   0.04737  -0.0160   0.0242   1.0000
  13.750   1.3495   0.05699   0.05074  -0.0161   0.0237   1.0000
  14.000   1.3457   0.06059   0.05454  -0.0165   0.0230   1.0000
  14.250   1.3422   0.06433   0.05847  -0.0170   0.0227   1.0000
  14.500   1.3364   0.06848   0.06281  -0.0179   0.0223   1.0000
  14.750   1.3290   0.07301   0.06753  -0.0192   0.0219   1.0000
  15.000   1.3204   0.07790   0.07262  -0.0208   0.0217   1.0000
  15.250   1.3098   0.08328   0.07820  -0.0230   0.0216   1.0000
  15.500   1.2975   0.08910   0.08424  -0.0256   0.0215   1.0000
  15.750   1.2830   0.09555   0.09089  -0.0288   0.0215   1.0000
  16.000   1.2674   0.10248   0.09802  -0.0325   0.0215   1.0000
  16.250   1.2497   0.11011   0.10584  -0.0369   0.0216   1.0000
  16.500   1.2300   0.11857   0.11450  -0.0421   0.0217   1.0000
  16.750   1.2084   0.12794   0.12407  -0.0480   0.0220   1.0000
  17.000   1.1840   0.13853   0.13485  -0.0549   0.0223   1.0000
  17.250   1.1560   0.15089   0.14737  -0.0630   0.0228   1.0000
  17.500   1.1226   0.16583   0.16244  -0.0726   0.0237   1.0000
  17.750   1.0860   0.18371   0.18039  -0.0831   0.0249   1.0000
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