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GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il)
Reynolds number: 500,000
Max Cl/Cd: 115.76 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe233-il-500000-n5.txt
Download as CSV file: xf-goe233-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 233 (MVA CA4) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1520   0.09185   0.08906  -0.0734   0.8745   0.0183
  -9.250  -0.2717   0.04421   0.04087  -0.1199   0.8465   0.0212
  -9.000  -0.2399   0.03641   0.03275  -0.1383   0.8388   0.0216
  -8.750  -0.1943   0.03054   0.02654  -0.1549   0.8316   0.0221
  -8.500  -0.1453   0.02627   0.02191  -0.1681   0.8256   0.0227
  -8.250  -0.0952   0.02297   0.01825  -0.1793   0.8199   0.0234
  -8.000  -0.0522   0.02074   0.01574  -0.1863   0.8141   0.0238
  -7.750  -0.0206   0.01961   0.01451  -0.1884   0.8085   0.0242
  -7.500   0.0126   0.01860   0.01342  -0.1907   0.8027   0.0245
  -7.250   0.0460   0.01768   0.01239  -0.1930   0.7962   0.0249
  -7.000   0.0789   0.01687   0.01145  -0.1949   0.7901   0.0253
  -6.750   0.1116   0.01617   0.01065  -0.1967   0.7836   0.0259
  -6.500   0.1438   0.01555   0.00992  -0.1981   0.7772   0.0264
  -6.250   0.1756   0.01500   0.00927  -0.1993   0.7713   0.0268
  -6.000   0.2072   0.01450   0.00868  -0.2004   0.7642   0.0271
  -5.750   0.2384   0.01407   0.00815  -0.2014   0.7573   0.0274
  -5.500   0.2698   0.01366   0.00767  -0.2024   0.7502   0.0277
  -5.250   0.3009   0.01332   0.00723  -0.2032   0.7425   0.0279
  -5.000   0.3326   0.01282   0.00670  -0.2043   0.7341   0.0284
  -4.750   0.3642   0.01241   0.00621  -0.2053   0.7237   0.0290
  -4.500   0.3957   0.01204   0.00577  -0.2063   0.7133   0.0296
  -4.250   0.4269   0.01172   0.00534  -0.2072   0.7043   0.0300
  -4.000   0.4582   0.01141   0.00496  -0.2080   0.6963   0.0305
  -3.500   0.5196   0.01093   0.00431  -0.2093   0.6815   0.0315
  -3.250   0.5498   0.01076   0.00404  -0.2098   0.6742   0.0320
  -3.000   0.5800   0.01062   0.00382  -0.2102   0.6678   0.0324
  -2.750   0.6101   0.01046   0.00359  -0.2107   0.6616   0.0332
  -2.250   0.6698   0.01024   0.00322  -0.2113   0.6497   0.0360
  -2.000   0.6993   0.01017   0.00310  -0.2116   0.6435   0.0377
  -1.750   0.7288   0.01010   0.00299  -0.2118   0.6373   0.0429
  -1.500   0.7586   0.00997   0.00290  -0.2122   0.6307   0.0741
  -1.250   0.7878   0.00992   0.00283  -0.2124   0.6243   0.0861
  -1.000   0.8177   0.00973   0.00274  -0.2129   0.6188   0.1384
  -0.750   0.8469   0.00967   0.00270  -0.2131   0.6124   0.1588
  -0.500   0.8759   0.00959   0.00267  -0.2133   0.6055   0.1951
  -0.250   0.9048   0.00955   0.00274  -0.2135   0.5992   0.2489
   0.000   0.9332   0.00961   0.00283  -0.2134   0.5930   0.2686
   0.250   0.9613   0.00972   0.00290  -0.2133   0.5877   0.2790
   0.500   0.9896   0.00980   0.00300  -0.2133   0.5827   0.2900
   0.750   1.0177   0.00991   0.00313  -0.2131   0.5765   0.3001
   1.000   1.0453   0.01006   0.00322  -0.2129   0.5699   0.3081
   1.250   1.0734   0.01014   0.00332  -0.2128   0.5637   0.3115
   1.500   1.1012   0.01025   0.00343  -0.2127   0.5565   0.3145
   1.750   1.1288   0.01037   0.00353  -0.2125   0.5492   0.3180
   2.000   1.1564   0.01048   0.00362  -0.2123   0.5406   0.3213
   2.250   1.1837   0.01061   0.00371  -0.2121   0.5318   0.3242
   2.500   1.2109   0.01074   0.00386  -0.2119   0.5228   0.3273
   2.750   1.2380   0.01089   0.00401  -0.2116   0.5148   0.3306
   3.000   1.2648   0.01105   0.00415  -0.2113   0.5046   0.3334
   3.250   1.2914   0.01122   0.00430  -0.2110   0.4929   0.3361
   3.500   1.3176   0.01142   0.00445  -0.2106   0.4823   0.3389
   3.750   1.3435   0.01163   0.00463  -0.2102   0.4706   0.3413
   4.000   1.3694   0.01183   0.00483  -0.2098   0.4588   0.3433
   4.250   1.3950   0.01206   0.00504  -0.2093   0.4485   0.3451
   4.500   1.4201   0.01231   0.00527  -0.2088   0.4372   0.3469
   4.750   1.4456   0.01254   0.00550  -0.2083   0.4264   0.3488
   5.000   1.4705   0.01280   0.00575  -0.2077   0.4166   0.3507
   5.250   1.4947   0.01309   0.00602  -0.2070   0.4040   0.3527
   5.500   1.5186   0.01342   0.00631  -0.2063   0.3888   0.3545
   5.750   1.5411   0.01382   0.00664  -0.2054   0.3701   0.3561
   6.000   1.5627   0.01428   0.00702  -0.2043   0.3449   0.3579
   6.250   1.5812   0.01495   0.00753  -0.2028   0.3096   0.3598
   6.500   1.5968   0.01581   0.00819  -0.2008   0.2729   0.3616
   6.750   1.6134   0.01655   0.00881  -0.1990   0.2491   0.3635
   7.000   1.6308   0.01720   0.00938  -0.1972   0.2335   0.3654
   7.250   1.6485   0.01777   0.00993  -0.1955   0.2235   0.3673
   7.500   1.6678   0.01820   0.01039  -0.1941   0.2168   0.3692
   7.750   1.6836   0.01878   0.01097  -0.1921   0.2088   0.3709
   8.000   1.6985   0.01923   0.01146  -0.1898   0.2029   0.3725
   8.250   1.7128   0.01977   0.01204  -0.1875   0.1963   0.3743
   8.500   1.7270   0.02041   0.01271  -0.1854   0.1892   0.3763
   8.750   1.7414   0.02107   0.01338  -0.1833   0.1790   0.3784
   9.000   1.7534   0.02189   0.01419  -0.1810   0.1650   0.3805
   9.250   1.7607   0.02305   0.01523  -0.1782   0.1426   0.3823
   9.500   1.7585   0.02491   0.01688  -0.1743   0.1078   0.3837
   9.750   1.7544   0.02703   0.01884  -0.1705   0.0815   0.3850
  10.000   1.7570   0.02877   0.02054  -0.1677   0.0676   0.3865
  10.250   1.7610   0.03046   0.02222  -0.1651   0.0577   0.3879
  10.500   1.7664   0.03211   0.02389  -0.1629   0.0509   0.3895
  10.750   1.7732   0.03368   0.02552  -0.1609   0.0464   0.3913
  11.000   1.7786   0.03543   0.02730  -0.1589   0.0426   0.3933
  11.250   1.7854   0.03708   0.02902  -0.1571   0.0400   0.3955
  11.500   1.7915   0.03883   0.03084  -0.1553   0.0377   0.3978
  11.750   1.7957   0.04081   0.03286  -0.1535   0.0355   0.3999
  12.000   1.8009   0.04274   0.03487  -0.1519   0.0338   0.4019
  12.250   1.8061   0.04468   0.03690  -0.1503   0.0323   0.4037
  12.500   1.8100   0.04681   0.03912  -0.1488   0.0308   0.4056
  12.750   1.8123   0.04917   0.04155  -0.1474   0.0293   0.4076
  13.000   1.8150   0.05156   0.04402  -0.1460   0.0280   0.4097
  13.250   1.8191   0.05383   0.04640  -0.1448   0.0269   0.4121
  13.500   1.8216   0.05633   0.04899  -0.1437   0.0255   0.4144
  13.750   1.8225   0.05908   0.05180  -0.1426   0.0244   0.4168
  14.000   1.8220   0.06206   0.05486  -0.1416   0.0233   0.4192
  14.250   1.8245   0.06472   0.05764  -0.1407   0.0224   0.4221
  14.500   1.8254   0.06759   0.06061  -0.1399   0.0213   0.4251
  14.750   1.8249   0.07070   0.06380  -0.1392   0.0202   0.4281
  15.000   1.8227   0.07408   0.06727  -0.1386   0.0192   0.4310
  15.500   1.8203   0.08070   0.07410  -0.1376   0.0175   0.4371
  15.750   1.8174   0.08428   0.07778  -0.1372   0.0167   0.4407
  16.000   1.8135   0.08805   0.08164  -0.1370   0.0160   0.4446
  16.250   1.8084   0.09204   0.08572  -0.1369   0.0154   0.4485
  16.500   1.8050   0.09585   0.08965  -0.1369   0.0149   0.4534
  16.750   1.8006   0.09985   0.09378  -0.1370   0.0144   0.4594
  17.250   1.7897   0.10826   0.10241  -0.1377   0.0135   0.4760
  17.500   1.7838   0.11261   0.10689  -0.1383   0.0131   0.4910
  17.750   1.7776   0.11710   0.11153  -0.1391   0.0127   0.5421
  18.000   1.7696   0.12135   0.11621  -0.1398   0.0124   1.0000
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