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GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il)
Reynolds number: 500,000
Max Cl/Cd: 96.98 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe309-il-500000.txt
Download as CSV file: xf-goe309-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 309 (MVA H.41) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -3.500  -0.0388   0.01967   0.01460  -0.0523   0.7759   0.0322
  -3.250  -0.0131   0.01696   0.01137  -0.0515   0.7670   0.0331
  -3.000   0.0144   0.01616   0.01025  -0.0512   0.7572   0.0350
  -2.750   0.0402   0.01376   0.00749  -0.0508   0.7482   0.0369
  -2.500   0.0674   0.01297   0.00652  -0.0506   0.7391   0.0382
  -2.250   0.0951   0.01245   0.00589  -0.0505   0.7293   0.0401
  -2.000   0.1228   0.01195   0.00529  -0.0503   0.7203   0.0418
  -1.750   0.1502   0.01142   0.00462  -0.0500   0.7113   0.0427
  -1.500   0.1778   0.01095   0.00406  -0.0499   0.7013   0.0436
  -1.250   0.2052   0.01060   0.00363  -0.0496   0.6918   0.0447
  -1.000   0.2327   0.01039   0.00333  -0.0495   0.6821   0.0459
  -0.750   0.2597   0.00992   0.00281  -0.0492   0.6718   0.0477
  -0.500   0.2870   0.00964   0.00249  -0.0490   0.6614   0.0508
  -0.250   0.3145   0.00950   0.00230  -0.0489   0.6503   0.0542
   0.000   0.3421   0.00940   0.00213  -0.0488   0.6378   0.0584
   0.250   0.3695   0.00925   0.00207  -0.0486   0.6239   0.0890
   0.500   0.3971   0.00922   0.00204  -0.0486   0.6091   0.1176
   0.750   0.4247   0.00920   0.00199  -0.0486   0.5940   0.1316
   1.000   0.4522   0.00918   0.00195  -0.0485   0.5786   0.1448
   1.250   0.4795   0.00912   0.00193  -0.0485   0.5626   0.1753
   1.500   0.5060   0.00890   0.00199  -0.0485   0.5472   0.3128
   1.750   0.5180   0.00738   0.00213  -0.0448   0.5356   0.9526
   2.000   0.5909   0.00764   0.00229  -0.0546   0.5183   0.9964
   2.250   0.6305   0.00779   0.00233  -0.0573   0.5050   1.0000
   2.500   0.6556   0.00791   0.00236  -0.0568   0.4941   1.0000
   2.750   0.6808   0.00800   0.00242  -0.0564   0.4839   1.0000
   3.000   0.7058   0.00811   0.00248  -0.0559   0.4745   1.0000
   3.500   0.7556   0.00836   0.00263  -0.0549   0.4564   1.0000
   3.750   0.7804   0.00849   0.00274  -0.0543   0.4479   1.0000
   4.000   0.8051   0.00863   0.00285  -0.0538   0.4389   1.0000
   4.250   0.8298   0.00877   0.00296  -0.0533   0.4266   1.0000
   4.500   0.8544   0.00893   0.00307  -0.0528   0.4126   1.0000
   4.750   0.8790   0.00910   0.00321  -0.0523   0.3986   1.0000
   5.000   0.9030   0.00932   0.00335  -0.0517   0.3773   1.0000
   5.250   0.9271   0.00956   0.00350  -0.0511   0.3527   1.0000
   5.500   0.9505   0.00990   0.00369  -0.0505   0.3194   1.0000
   5.750   0.9717   0.01051   0.00403  -0.0497   0.2649   1.0000
   6.000   0.9913   0.01135   0.00452  -0.0487   0.2079   1.0000
   6.250   1.0117   0.01212   0.00501  -0.0478   0.1639   1.0000
   6.500   1.0261   0.01356   0.00586  -0.0462   0.0733   1.0000
   6.750   1.0431   0.01471   0.00676  -0.0448   0.0215   1.0000
   7.000   1.0662   0.01515   0.00730  -0.0441   0.0190   1.0000
   7.250   1.0885   0.01567   0.00793  -0.0433   0.0175   1.0000
   7.500   1.1098   0.01629   0.00865  -0.0424   0.0164   1.0000
   7.750   1.1295   0.01706   0.00954  -0.0413   0.0154   1.0000
   8.000   1.1461   0.01809   0.01070  -0.0397   0.0147   1.0000
   8.250   1.1601   0.01929   0.01204  -0.0378   0.0142   1.0000
   8.500   1.1792   0.01994   0.01275  -0.0367   0.0136   1.0000
   8.750   1.1941   0.02089   0.01379  -0.0351   0.0132   1.0000
   9.000   1.2062   0.02199   0.01498  -0.0330   0.0129   1.0000
   9.250   1.2150   0.02315   0.01623  -0.0305   0.0126   1.0000
   9.500   1.2198   0.02441   0.01758  -0.0275   0.0124   1.0000
   9.750   1.2241   0.02586   0.01912  -0.0249   0.0122   1.0000
  10.000   1.2282   0.02747   0.02082  -0.0225   0.0121   1.0000
  10.250   1.2326   0.02924   0.02267  -0.0204   0.0121   1.0000
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