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GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il)
Reynolds number: 200,000
Max Cl/Cd: 79.4 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe234-il-200000-n5.txt
Download as CSV file: xf-goe234-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 234 (MVA CA5) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.0469   0.10181   0.09780  -0.0963   0.9152   0.0334
 -10.250  -0.0433   0.09775   0.09371  -0.0982   0.9087   0.0336
  -9.750  -0.0404   0.08896   0.08489  -0.1026   0.8938   0.0349
  -9.500  -0.0272   0.08763   0.08355  -0.1030   0.8864   0.0356
  -9.250  -0.0187   0.08502   0.08091  -0.1041   0.8799   0.0364
  -9.000  -0.0145   0.08126   0.07713  -0.1061   0.8733   0.0368
  -8.500  -0.0921   0.05156   0.04716  -0.1324   0.8539   0.0384
  -8.250  -0.0484   0.03419   0.02881  -0.1758   0.8464   0.0397
  -8.000   0.0006   0.03017   0.02440  -0.1882   0.8424   0.0405
  -7.750   0.0358   0.02867   0.02282  -0.1925   0.8370   0.0414
  -7.500   0.0743   0.02712   0.02113  -0.1975   0.8322   0.0425
  -7.250   0.1141   0.02556   0.01935  -0.2025   0.8280   0.0438
  -7.000   0.1517   0.02423   0.01782  -0.2064   0.8235   0.0449
  -6.750   0.1873   0.02318   0.01659  -0.2093   0.8181   0.0459
  -6.500   0.2210   0.02240   0.01566  -0.2112   0.8132   0.0468
  -6.250   0.2501   0.02199   0.01524  -0.2115   0.8088   0.0480
  -6.000   0.2817   0.02153   0.01477  -0.2128   0.8033   0.0494
  -5.750   0.3133   0.02111   0.01431  -0.2139   0.7977   0.0510
  -5.500   0.3442   0.02081   0.01393  -0.2146   0.7928   0.0524
  -5.250   0.3751   0.02056   0.01359  -0.2152   0.7881   0.0538
  -5.000   0.4036   0.02050   0.01358  -0.2152   0.7817   0.0553
  -4.750   0.4348   0.02029   0.01339  -0.2160   0.7760   0.0575
  -4.500   0.4669   0.02009   0.01312  -0.2171   0.7714   0.0603
  -4.250   0.4984   0.01992   0.01292  -0.2181   0.7652   0.0629
  -4.000   0.5311   0.01973   0.01275  -0.2193   0.7589   0.0662
  -3.750   0.5666   0.01930   0.01222  -0.2215   0.7537   0.0706
  -3.500   0.6054   0.01859   0.01146  -0.2250   0.7473   0.0774
  -3.250   0.6481   0.01753   0.01033  -0.2297   0.7411   0.0911
  -3.000   0.6914   0.01641   0.00969  -0.2348   0.7357   0.2121
  -2.750   0.7184   0.01670   0.01002  -0.2343   0.7285   0.2453
  -2.500   0.7564   0.01579   0.00883  -0.2375   0.7219   0.2688
  -2.250   0.7803   0.01646   0.00953  -0.2358   0.7162   0.2737
  -2.000   0.8117   0.01631   0.00925  -0.2368   0.7088   0.2849
  -1.750   0.8365   0.01683   0.00977  -0.2354   0.7023   0.2873
  -1.250   0.8954   0.01689   0.00966  -0.2360   0.6886   0.3000
  -1.000   0.9193   0.01746   0.01025  -0.2345   0.6823   0.3019
  -0.750   0.9435   0.01793   0.01076  -0.2332   0.6742   0.3047
  -0.500   0.9786   0.01744   0.01000  -0.2353   0.6666   0.3140
  -0.250   1.0061   0.01751   0.01005  -0.2351   0.6577   0.3154
   0.000   1.0332   0.01762   0.01008  -0.2348   0.6492   0.3165
   0.250   1.0601   0.01772   0.01016  -0.2345   0.6392   0.3179
   0.500   1.0871   0.01781   0.01016  -0.2342   0.6287   0.3195
   0.750   1.1141   0.01789   0.01016  -0.2340   0.6172   0.3216
   1.000   1.1424   0.01789   0.01009  -0.2342   0.6074   0.3247
   1.250   1.1755   0.01753   0.00950  -0.2358   0.5996   0.3303
   1.500   1.2028   0.01760   0.00955  -0.2357   0.5928   0.3311
   1.750   1.2299   0.01768   0.00963  -0.2356   0.5857   0.3319
   2.000   1.2570   0.01779   0.00969  -0.2354   0.5792   0.3329
   2.250   1.2840   0.01787   0.00980  -0.2353   0.5721   0.3340
   2.500   1.3107   0.01797   0.00988  -0.2352   0.5649   0.3353
   2.750   1.3375   0.01808   0.00996  -0.2350   0.5581   0.3368
   3.000   1.3640   0.01818   0.01006  -0.2348   0.5504   0.3387
   3.500   1.4171   0.01836   0.01018  -0.2346   0.5349   0.3440
   3.750   1.4432   0.01847   0.01020  -0.2344   0.5265   0.3462
   4.000   1.4676   0.01865   0.01043  -0.2338   0.5175   0.3472
   4.250   1.4911   0.01889   0.01065  -0.2330   0.5081   0.3482
   4.500   1.5146   0.01910   0.01090  -0.2322   0.4976   0.3495
   4.750   1.5371   0.01936   0.01116  -0.2312   0.4873   0.3508
   5.000   1.5589   0.01964   0.01145  -0.2302   0.4759   0.3524
   5.250   1.5803   0.01993   0.01174  -0.2290   0.4643   0.3541
   5.500   1.6002   0.02028   0.01207  -0.2276   0.4521   0.3563
   5.750   1.6184   0.02068   0.01243  -0.2260   0.4386   0.3588
   6.000   1.6354   0.02112   0.01280  -0.2241   0.4230   0.3613
   6.250   1.6490   0.02166   0.01332  -0.2216   0.4064   0.3626
   6.500   1.6587   0.02230   0.01391  -0.2185   0.3899   0.3636
   6.750   1.6642   0.02303   0.01462  -0.2146   0.3739   0.3646
   7.000   1.6729   0.02388   0.01544  -0.2115   0.3582   0.3658
   7.250   1.6826   0.02479   0.01631  -0.2088   0.3443   0.3672
   7.500   1.6924   0.02574   0.01724  -0.2062   0.3325   0.3687
   7.750   1.7019   0.02676   0.01823  -0.2036   0.3219   0.3704
   8.000   1.7136   0.02769   0.01918  -0.2014   0.3128   0.3723
   8.500   1.7353   0.02976   0.02126  -0.1971   0.2973   0.3767
   8.750   1.7456   0.03087   0.02241  -0.1949   0.2906   0.3782
   9.000   1.7555   0.03204   0.02363  -0.1928   0.2841   0.3796
   9.250   1.7657   0.03322   0.02486  -0.1908   0.2765   0.3811
   9.500   1.7724   0.03468   0.02632  -0.1885   0.2698   0.3826
   9.750   1.7842   0.03581   0.02754  -0.1868   0.2634   0.3843
  10.000   1.7928   0.03720   0.02898  -0.1849   0.2571   0.3861
  10.250   1.8003   0.03872   0.03053  -0.1829   0.2520   0.3879
  10.500   1.8118   0.03995   0.03186  -0.1814   0.2468   0.3899
  10.750   1.8199   0.04147   0.03343  -0.1796   0.2408   0.3919
  11.000   1.8245   0.04329   0.03527  -0.1775   0.2354   0.3935
  11.250   1.8338   0.04475   0.03687  -0.1760   0.2286   0.3952
  11.500   1.8387   0.04662   0.03881  -0.1742   0.2217   0.3969
  11.750   1.8439   0.04852   0.04079  -0.1725   0.2161   0.3988
  12.000   1.8509   0.05029   0.04267  -0.1710   0.2088   0.4008
  12.250   1.8520   0.05270   0.04510  -0.1692   0.2014   0.4025
  12.500   1.8576   0.05474   0.04724  -0.1678   0.1908   0.4045
  12.750   1.8583   0.05734   0.04989  -0.1663   0.1760   0.4062
  13.000   1.8449   0.06161   0.05400  -0.1644   0.1414   0.4072
  13.250   1.8198   0.06739   0.05952  -0.1624   0.1110   0.4077
  13.500   1.8044   0.07221   0.06429  -0.1608   0.0939   0.4085
  13.750   1.7914   0.07689   0.06896  -0.1596   0.0758   0.4093
  14.000   1.7708   0.08270   0.07468  -0.1586   0.0536   0.4099
  14.250   1.7570   0.08778   0.07978  -0.1580   0.0460   0.4108
  14.500   1.7477   0.09238   0.08446  -0.1576   0.0427   0.4119
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