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GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 474 AIRFOIL (goe474-il)
Reynolds number: 200,000
Max Cl/Cd: 77.12 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe474-il-200000.txt
Download as CSV file: xf-goe474-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 474 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4293   0.08817   0.08462  -0.0266   1.0000   0.0529
  -8.000  -0.4334   0.08523   0.08176  -0.0276   1.0000   0.0550
  -7.750  -0.4470   0.08238   0.07901  -0.0298   1.0000   0.0567
  -7.500  -0.4559   0.07793   0.07456  -0.0388   1.0000   0.0579
  -7.250  -0.4600   0.07279   0.06946  -0.0387   1.0000   0.0588
  -7.000  -0.4549   0.07081   0.06753  -0.0346   1.0000   0.0600
  -6.750  -0.4510   0.06873   0.06547  -0.0325   1.0000   0.0614
  -6.500  -0.4488   0.06652   0.06327  -0.0314   1.0000   0.0638
  -6.250  -0.4490   0.06159   0.05798  -0.0388   1.0000   0.0700
  -6.000  -0.4506   0.05764   0.05419  -0.0355   1.0000   0.0715
  -5.750  -0.4457   0.05650   0.05312  -0.0320   1.0000   0.0733
  -5.500  -0.4395   0.05426   0.05085  -0.0306   1.0000   0.0760
  -5.250  -0.4355   0.03367   0.02910  -0.0364   1.0000   0.0440
  -5.000  -0.4234   0.02516   0.01948  -0.0356   1.0000   0.0401
  -4.750  -0.3907   0.02164   0.01523  -0.0370   0.9971   0.0406
  -4.500  -0.3553   0.02014   0.01332  -0.0387   0.9938   0.0444
  -4.250  -0.3213   0.01867   0.01143  -0.0397   0.9900   0.0464
  -4.000  -0.2884   0.01680   0.00937  -0.0409   0.9869   0.0501
  -3.750  -0.2508   0.01616   0.00861  -0.0429   0.9837   0.0564
  -3.500  -0.2189   0.01523   0.00764  -0.0438   0.9787   0.0620
  -3.250  -0.1833   0.01475   0.00714  -0.0454   0.9741   0.0725
  -3.000  -0.1447   0.01441   0.00687  -0.0476   0.9708   0.0915
  -2.750  -0.1127   0.01446   0.00694  -0.0484   0.9645   0.1280
  -2.500  -0.0755   0.01457   0.00696  -0.0505   0.9597   0.1487
  -2.250  -0.0355   0.01452   0.00686  -0.0531   0.9566   0.1633
  -2.000  -0.0068   0.01440   0.00674  -0.0534   0.9495   0.1746
  -1.750   0.0298   0.01417   0.00649  -0.0553   0.9455   0.1846
  -1.500   0.0700   0.01400   0.00629  -0.0579   0.9428   0.1958
  -1.250   0.0981   0.01374   0.00612  -0.0581   0.9356   0.2063
  -1.000   0.1350   0.01342   0.00587  -0.0599   0.9317   0.2174
  -0.750   0.1749   0.01307   0.00562  -0.0624   0.9292   0.2308
  -0.500   0.2057   0.01279   0.00544  -0.0630   0.9223   0.2469
  -0.250   0.2438   0.01223   0.00512  -0.0649   0.9168   0.2855
   0.000   0.3404   0.01001   0.00490  -0.0788   0.9222   1.0000
   0.250   0.3790   0.00983   0.00463  -0.0806   0.9157   1.0000
   0.500   0.4092   0.00972   0.00447  -0.0807   0.9053   1.0000
   0.750   0.4405   0.00954   0.00424  -0.0807   0.8939   1.0000
   1.000   0.4686   0.00938   0.00402  -0.0800   0.8806   1.0000
   1.250   0.4946   0.00928   0.00388  -0.0790   0.8672   1.0000
   1.500   0.5206   0.00924   0.00379  -0.0780   0.8553   1.0000
   1.750   0.5444   0.00925   0.00379  -0.0768   0.8424   1.0000
   2.000   0.5682   0.00922   0.00373  -0.0754   0.8275   1.0000
   2.250   0.5907   0.00920   0.00368  -0.0737   0.8092   1.0000
   2.500   0.6136   0.00920   0.00365  -0.0721   0.7904   1.0000
   2.750   0.6372   0.00922   0.00367  -0.0707   0.7727   1.0000
   3.000   0.6611   0.00926   0.00368  -0.0694   0.7544   1.0000
   3.250   0.6837   0.00932   0.00375  -0.0679   0.7319   1.0000
   3.500   0.7064   0.00939   0.00379  -0.0664   0.7059   1.0000
   3.750   0.7283   0.00951   0.00385  -0.0647   0.6716   1.0000
   4.000   0.7488   0.00971   0.00391  -0.0627   0.6245   1.0000
   4.250   0.7668   0.01007   0.00401  -0.0603   0.5477   1.0000
   4.500   0.7782   0.01092   0.00423  -0.0569   0.4315   1.0000
   4.750   0.7918   0.01185   0.00472  -0.0542   0.3505   1.0000
   5.000   0.8078   0.01271   0.00524  -0.0521   0.2828   1.0000
   5.250   0.8252   0.01352   0.00576  -0.0503   0.2358   1.0000
   5.500   0.8442   0.01423   0.00630  -0.0488   0.2044   1.0000
   5.750   0.8639   0.01491   0.00685  -0.0474   0.1828   1.0000
   6.000   0.8838   0.01561   0.00748  -0.0461   0.1665   1.0000
   6.250   0.9048   0.01619   0.00803  -0.0449   0.1514   1.0000
   6.500   0.9264   0.01667   0.00852  -0.0439   0.1367   1.0000
   6.750   0.9481   0.01712   0.00901  -0.0429   0.1222   1.0000
   7.000   0.9699   0.01755   0.00948  -0.0419   0.1053   1.0000
   7.250   0.9885   0.01835   0.01020  -0.0404   0.0840   1.0000
   7.500   1.0072   0.01923   0.01104  -0.0389   0.0612   1.0000
   7.750   1.0241   0.02035   0.01210  -0.0371   0.0491   1.0000
   8.000   1.0417   0.02151   0.01335  -0.0352   0.0430   1.0000
   8.250   1.0566   0.02314   0.01494  -0.0333   0.0384   1.0000
   8.500   1.0757   0.02431   0.01628  -0.0318   0.0352   1.0000
   8.750   1.0943   0.02572   0.01783  -0.0304   0.0328   1.0000
   9.000   1.1125   0.02736   0.01954  -0.0290   0.0309   1.0000
   9.250   1.1309   0.03022   0.02254  -0.0279   0.0293   1.0000
   9.500   1.1468   0.03273   0.02537  -0.0263   0.0282   1.0000
   9.750   1.1611   0.03441   0.02736  -0.0244   0.0270   1.0000
  10.000   1.1724   0.03676   0.03004  -0.0222   0.0260   1.0000
  10.250   1.1797   0.03956   0.03321  -0.0197   0.0255   1.0000
  10.500   1.1814   0.04275   0.03680  -0.0168   0.0254   1.0000
  10.750   1.1767   0.04615   0.04060  -0.0135   0.0253   1.0000
  11.000   1.1641   0.04946   0.04425  -0.0093   0.0254   1.0000
  11.250   1.1468   0.05297   0.04806  -0.0056   0.0256   1.0000
  11.500   1.1273   0.05676   0.05212  -0.0028   0.0259   1.0000
  11.750   1.1050   0.06111   0.05672  -0.0012   0.0261   1.0000
  12.000   1.0827   0.06585   0.06166  -0.0011   0.0264   1.0000
  12.250   1.0583   0.07147   0.06748  -0.0026   0.0266   1.0000
  12.500   1.0327   0.07820   0.07437  -0.0059   0.0268   1.0000
  12.750   1.0062   0.08635   0.08268  -0.0112   0.0271   1.0000
  13.000   0.9774   0.09698   0.09343  -0.0189   0.0276   1.0000
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