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GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il)
Reynolds number: 200,000
Max Cl/Cd: 69.39 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe243-il-200000-n5.txt
Download as CSV file: xf-goe243-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 243 (MVA PR.3) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.1235   0.09441   0.08982  -0.1144   0.8197   0.0434
  -9.500   0.1284   0.08525   0.08059  -0.1185   0.8078   0.0387
  -9.250   0.1347   0.08200   0.07728  -0.1201   0.8025   0.0386
  -9.000   0.1349   0.07723   0.07251  -0.1230   0.7965   0.0387
  -8.750   0.1374   0.07307   0.06833  -0.1255   0.7903   0.0386
  -8.500   0.1411   0.06925   0.06448  -0.1277   0.7846   0.0384
  -8.250   0.1365   0.06333   0.05849  -0.1316   0.7795   0.0380
  -8.000   0.0669   0.04580   0.04064  -0.1507   0.7709   0.0369
  -7.750   0.0750   0.03744   0.03180  -0.1684   0.7639   0.0367
  -7.500   0.1106   0.03252   0.02640  -0.1816   0.7582   0.0369
  -7.250   0.1482   0.02942   0.02297  -0.1901   0.7506   0.0372
  -7.000   0.1856   0.02719   0.02040  -0.1958   0.7437   0.0376
  -6.750   0.2217   0.02552   0.01841  -0.1996   0.7382   0.0380
  -6.500   0.2546   0.02425   0.01694  -0.2022   0.7319   0.0384
  -6.250   0.2863   0.02331   0.01588  -0.2040   0.7258   0.0390
  -6.000   0.3175   0.02265   0.01517  -0.2053   0.7205   0.0396
  -5.750   0.3491   0.02202   0.01447  -0.2066   0.7154   0.0403
  -5.500   0.3793   0.02142   0.01383  -0.2076   0.7091   0.0409
  -5.250   0.4098   0.02083   0.01316  -0.2084   0.7032   0.0414
  -5.000   0.4408   0.02028   0.01251  -0.2092   0.6979   0.0420
  -4.750   0.4708   0.01982   0.01201  -0.2098   0.6919   0.0426
  -4.500   0.5010   0.01942   0.01156  -0.2104   0.6855   0.0432
  -4.250   0.5321   0.01903   0.01116  -0.2112   0.6797   0.0439
  -4.000   0.5643   0.01868   0.01080  -0.2124   0.6740   0.0448
  -3.750   0.5961   0.01836   0.01049  -0.2135   0.6670   0.0458
  -3.500   0.6291   0.01806   0.01013  -0.2148   0.6604   0.0472
  -3.250   0.6631   0.01776   0.00977  -0.2164   0.6546   0.0490
  -3.000   0.6965   0.01748   0.00952  -0.2180   0.6473   0.0511
  -2.750   0.7306   0.01722   0.00917  -0.2196   0.6401   0.0534
  -2.500   0.7652   0.01695   0.00882  -0.2214   0.6333   0.0559
  -2.250   0.7981   0.01674   0.00856  -0.2228   0.6256   0.0596
  -2.000   0.8313   0.01654   0.00828  -0.2241   0.6184   0.0653
  -1.750   0.8637   0.01635   0.00806  -0.2253   0.6106   0.0761
  -1.500   0.8960   0.01613   0.00781  -0.2265   0.6012   0.0989
  -1.250   0.9340   0.01548   0.00757  -0.2296   0.5918   0.2790
  -1.000   0.9619   0.01558   0.00767  -0.2296   0.5819   0.3068
  -0.750   0.9894   0.01573   0.00774  -0.2295   0.5732   0.3257
  -0.500   1.0162   0.01592   0.00791  -0.2292   0.5634   0.3464
  -0.250   1.0425   0.01616   0.00802  -0.2288   0.5540   0.3630
   0.000   1.0678   0.01634   0.00824  -0.2282   0.5430   0.3722
   0.250   1.0930   0.01657   0.00835  -0.2277   0.5325   0.3806
   0.500   1.1183   0.01677   0.00846  -0.2272   0.5213   0.3874
   0.750   1.1428   0.01698   0.00863  -0.2265   0.5119   0.3921
   1.000   1.1675   0.01719   0.00879  -0.2259   0.5022   0.3963
   1.250   1.1915   0.01743   0.00894  -0.2253   0.4934   0.4007
   1.500   1.2158   0.01767   0.00911  -0.2246   0.4843   0.4054
   1.750   1.2386   0.01796   0.00929  -0.2238   0.4762   0.4098
   2.000   1.2620   0.01820   0.00956  -0.2230   0.4682   0.4142
   2.250   1.2841   0.01851   0.00983  -0.2220   0.4606   0.4191
   2.500   1.3062   0.01883   0.01010  -0.2210   0.4538   0.4247
   2.750   1.3282   0.01914   0.01036  -0.2201   0.4464   0.4311
   3.000   1.3477   0.01952   0.01072  -0.2187   0.4394   0.4365
   3.250   1.3669   0.01987   0.01108  -0.2172   0.4333   0.4426
   3.500   1.3855   0.02023   0.01143  -0.2157   0.4271   0.4494
   3.750   1.4039   0.02066   0.01182  -0.2142   0.4209   0.4559
   4.000   1.4229   0.02112   0.01228  -0.2128   0.4155   0.4616
   4.250   1.4429   0.02154   0.01274  -0.2116   0.4100   0.4684
   4.500   1.4619   0.02202   0.01319  -0.2104   0.4044   0.4761
   4.750   1.4790   0.02259   0.01375  -0.2088   0.3992   0.4822
   5.000   1.4973   0.02310   0.01430  -0.2074   0.3934   0.4894
   5.250   1.5144   0.02367   0.01487  -0.2060   0.3868   0.4979
   5.500   1.5299   0.02434   0.01553  -0.2043   0.3810   0.5039
   5.750   1.5467   0.02496   0.01618  -0.2028   0.3761   0.5105
   6.000   1.5643   0.02556   0.01681  -0.2016   0.3709   0.5182
   6.250   1.5793   0.02629   0.01755  -0.2000   0.3648   0.5241
   6.500   1.5921   0.02715   0.01839  -0.1981   0.3591   0.5298
   6.750   1.6088   0.02783   0.01913  -0.1968   0.3538   0.5372
   7.000   1.6236   0.02864   0.01996  -0.1953   0.3483   0.5438
   7.250   1.6360   0.02957   0.02091  -0.1936   0.3429   0.5490
   7.500   1.6496   0.03048   0.02186  -0.1921   0.3378   0.5551
   7.750   1.6638   0.03140   0.02280  -0.1907   0.3318   0.5617
   8.000   1.6746   0.03251   0.02395  -0.1890   0.3257   0.5659
   8.250   1.6854   0.03366   0.02512  -0.1873   0.3199   0.5709
   8.500   1.6970   0.03480   0.02632  -0.1859   0.3131   0.5769
   8.750   1.7051   0.03622   0.02773  -0.1841   0.3061   0.5824
   9.000   1.7146   0.03755   0.02911  -0.1826   0.2991   0.5865
   9.250   1.7215   0.03911   0.03070  -0.1808   0.2908   0.5911
   9.500   1.7278   0.04078   0.03238  -0.1792   0.2827   0.5963
   9.750   1.7322   0.04268   0.03429  -0.1775   0.2732   0.6012
  10.000   1.7365   0.04462   0.03625  -0.1759   0.2636   0.6048
  10.250   1.7370   0.04696   0.03860  -0.1741   0.2536   0.6087
  10.500   1.7385   0.04931   0.04095  -0.1725   0.2429   0.6132
  10.750   1.7385   0.05187   0.04350  -0.1710   0.2332   0.6176
  11.250   1.7362   0.05740   0.04905  -0.1681   0.2167   0.6244
  11.500   1.7338   0.06038   0.05204  -0.1668   0.2104   0.6280
  11.750   1.7345   0.06309   0.05479  -0.1656   0.2056   0.6320
  12.000   1.7349   0.06589   0.05762  -0.1646   0.2014   0.6361
  12.250   1.7342   0.06885   0.06061  -0.1636   0.1978   0.6396
  12.500   1.7325   0.07192   0.06372  -0.1626   0.1948   0.6426
  12.750   1.7358   0.07444   0.06631  -0.1618   0.1924   0.6464
  13.000   1.7380   0.07712   0.06905  -0.1610   0.1902   0.6503
  13.250   1.7407   0.07976   0.07174  -0.1603   0.1881   0.6544
  13.500   1.7428   0.08247   0.07450  -0.1597   0.1863   0.6581
  13.750   1.7453   0.08512   0.07721  -0.1590   0.1847   0.6615
  14.000   1.7482   0.08769   0.07982  -0.1584   0.1834   0.6654
  14.250   1.7515   0.09022   0.08238  -0.1579   0.1821   0.6695
  14.500   1.7567   0.09247   0.08464  -0.1573   0.1809   0.6738
  14.750   1.7638   0.09451   0.08676  -0.1568   0.1800   0.6779
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