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GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il)
Reynolds number: 50,000
Max Cl/Cd: 5.66 at α=-0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe243-il-50000.txt
Download as CSV file: xf-goe243-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2246   0.15647   0.15101  -0.0226   0.9718   0.2326
  -7.500  -0.2102   0.15513   0.14965  -0.0261   0.9634   0.2426
  -7.250  -0.2507   0.15912   0.15375  -0.0248   0.9610   0.2451
  -7.000  -0.1794   0.14975   0.14430  -0.0300   0.9452   0.2551
  -6.750  -0.1994   0.15138   0.14600  -0.0296   0.9399   0.2619
  -6.500  -0.1714   0.14680   0.14142  -0.0327   0.9299   0.2669
  -6.250  -0.1570   0.14449   0.13911  -0.0333   0.9208   0.2740
  -6.000  -0.1859   0.14780   0.14250  -0.0335   0.9164   0.2812
  -5.750  -0.1738   0.14357   0.13830  -0.0326   0.9065   0.2841
  -5.500  -0.1335   0.13933   0.13401  -0.0364   0.8958   0.2930
  -5.250  -0.1594   0.14046   0.13524  -0.0328   0.8891   0.2985
  -5.000  -0.2162   0.14507   0.13999  -0.0274   0.8883   0.3009
  -4.750  -0.1511   0.13654   0.13138  -0.0327   0.8728   0.3065
  -4.500  -0.1437   0.13484   0.12971  -0.0324   0.8646   0.3123
  -4.250  -0.3450   0.14894   0.14437  -0.0053   0.9563   0.3016
  -4.000  -0.2016   0.13823   0.13327  -0.0289   0.8579   0.3221
  -3.750  -0.2007   0.13524   0.13033  -0.0254   0.8518   0.3236
  -3.500  -0.1616   0.13086   0.12589  -0.0281   0.8377   0.3293
  -3.250  -0.1769   0.13062   0.12573  -0.0249   0.8341   0.3328
  -3.000  -0.1934   0.13125   0.12643  -0.0241   0.8362   0.3389
  -2.250   0.2054   0.07250   0.06457  -0.1780   0.7907   0.1573
  -2.000   0.2900   0.07127   0.06276  -0.1869   0.7796   0.1638
  -1.750   0.2834   0.07262   0.06413  -0.1846   0.7710   0.1648
  -1.500   0.3156   0.07302   0.06463  -0.1856   0.7630   0.1693
  -1.250   0.3450   0.07383   0.06541  -0.1866   0.7543   0.1754
  -1.000   0.3598   0.07510   0.06675  -0.1867   0.7466   0.1821
  -0.750   0.4258   0.07517   0.06709  -0.1919   0.7368   0.2111
  -0.500   0.4187   0.07763   0.06982  -0.1904   0.7317   0.2202
  -0.250   0.4334   0.07963   0.07225  -0.1906   0.7262   0.2582
   0.000   0.4608   0.08183   0.07483  -0.1868   0.7188   0.3684
   0.250   0.4491   0.08492   0.07804  -0.1813   0.7154   0.3933
   0.500   0.4268   0.08999   0.08326  -0.1815   0.7401   0.3937
   1.250   0.3770   0.09979   0.09332  -0.1731   0.7869   0.4322
   1.500   0.3728   0.10276   0.09641  -0.1639   0.7816   0.4615
   1.750   0.3756   0.10619   0.09980  -0.1580   0.7784   0.4948
   2.000   0.3585   0.10596   0.09964  -0.1522   0.7680   0.5036
   2.250   0.3670   0.10827   0.10190  -0.1469   0.7617   0.5356
   2.500   0.3841   0.11171   0.10528  -0.1428   0.7586   0.5712
   2.750   0.3657   0.11108   0.10469  -0.1394   0.7508   0.5770
   3.000   0.3757   0.11245   0.10603  -0.1363   0.7433   0.6055
   3.250   0.3957   0.11484   0.10837  -0.1335   0.7390   0.6440
   3.500   0.3896   0.11542   0.10894  -0.1317   0.7320   0.6558
   3.750   0.4040   0.11656   0.11004  -0.1311   0.7239   0.6718
   4.000   0.4546   0.12078   0.11406  -0.1378   0.7186   0.6753
   4.250   0.4513   0.12144   0.11472  -0.1374   0.7108   0.6747
   4.500   0.4841   0.12393   0.11709  -0.1414   0.7015   0.6749
   4.750   0.5343   0.12876   0.12178  -0.1469   0.6973   0.6785
   5.000   0.5156   0.12783   0.12092  -0.1444   0.6863   0.6789
   5.250   0.5622   0.13171   0.12468  -0.1493   0.6783   0.6833
   5.500   0.5592   0.13243   0.12541  -0.1489   0.6667   0.6847
   5.750   0.6224   0.13793   0.13074  -0.1557   0.6565   0.6896
   6.000   0.6193   0.13773   0.13055  -0.1552   0.6406   0.6913
   6.250   0.6296   0.13982   0.13265  -0.1561   0.6294   0.6947
   6.500   0.6848   0.14420   0.13692  -0.1605   0.6172   0.7043
   6.750   0.6733   0.14455   0.13731  -0.1597   0.6027   0.7066
   7.000   0.6916   0.14764   0.14038  -0.1616   0.5922   0.7121
   7.250   0.7476   0.15205   0.14466  -0.1654   0.5771   0.7225
   7.500   0.7371   0.15259   0.14525  -0.1650   0.5610   0.7250
   7.750   0.7405   0.15534   0.14801  -0.1659   0.5502   0.7297
   8.000   0.7985   0.16018   0.15272  -0.1693   0.5379   0.7448
   8.250   0.7696   0.16101   0.15364  -0.1689   0.5275   0.7451
   8.500   0.8211   0.16597   0.15847  -0.1718   0.5182   0.7602
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