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GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il)
Reynolds number: 50,000
Max Cl/Cd: 6.01 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe242-il-50000.txt
Download as CSV file: xf-goe242-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 242 (MVA PR.2) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2140   0.13926   0.13400  -0.0491   0.9552   0.2288
  -8.250  -0.1688   0.13115   0.12581  -0.0497   0.9480   0.2380
  -8.000  -0.1886   0.13338   0.12811  -0.0535   0.9400   0.2456
  -7.750  -0.1492   0.12660   0.12127  -0.0536   0.9326   0.2576
  -7.500  -0.1393   0.12407   0.11875  -0.0560   0.9259   0.2660
  -7.250  -0.1405   0.12330   0.11801  -0.0556   0.9179   0.2760
  -7.000  -0.1324   0.12073   0.11544  -0.0562   0.9114   0.2823
  -6.750  -0.1351   0.12035   0.11508  -0.0567   0.9058   0.2928
  -6.500  -0.1466   0.11950   0.11430  -0.0536   0.8986   0.2961
  -6.250  -0.1317   0.11698   0.11176  -0.0543   0.8934   0.3063
  -6.000  -0.1613   0.11837   0.11326  -0.0509   0.8880   0.3107
  -5.750  -0.1469   0.11536   0.11024  -0.0492   0.8832   0.3174
  -5.500  -0.1787   0.11707   0.11205  -0.0447   0.8803   0.3239
  -5.250  -0.1662   0.11423   0.10921  -0.0444   0.8771   0.3311
  -5.000  -0.1897   0.11544   0.11050  -0.0423   0.8751   0.3402
  -4.750  -0.1879   0.11320   0.10829  -0.0397   0.8727   0.3450
  -4.500  -0.1992   0.11287   0.10801  -0.0366   0.8724   0.3527
  -4.250  -0.2460   0.11533   0.11063  -0.0317   0.8800   0.3564
  -4.000  -0.0092   0.06466   0.05793  -0.1527   0.8697   0.1447
  -3.750   0.0591   0.06084   0.05335  -0.1656   0.8655   0.1435
  -3.500   0.1319   0.05849   0.05020  -0.1760   0.8597   0.1460
  -3.250   0.1719   0.05791   0.04920  -0.1795   0.8564   0.1477
  -3.000  -0.1657   0.06562   0.05950  -0.1212   1.0000   0.1458
  -2.750  -0.1033   0.06238   0.05558  -0.1332   1.0000   0.1409
  -2.500  -0.0541   0.06115   0.05377  -0.1406   1.0000   0.1423
  -2.250  -0.0111   0.06079   0.05292  -0.1458   0.9995   0.1447
  -2.000   0.0340   0.06108   0.05279  -0.1504   0.9968   0.1466
  -1.750   0.0751   0.06185   0.05346  -0.1538   0.9944   0.1510
  -1.500   0.1080   0.06277   0.05433  -0.1561   0.9911   0.1597
  -1.250   0.1482   0.06404   0.05563  -0.1595   0.9861   0.1710
  -1.000   0.1977   0.06590   0.05753  -0.1649   0.9829   0.1923
  -0.750   0.2403   0.06674   0.05946  -0.1702   0.9774   0.2817
  -0.500   0.2441   0.07023   0.06345  -0.1634   0.9677   0.4563
  -0.250   0.2475   0.07314   0.06634  -0.1565   0.9562   0.5076
   0.000   0.2473   0.07465   0.06783  -0.1506   0.9456   0.5392
   0.250   0.2638   0.07783   0.07094  -0.1465   0.9393   0.5858
   0.500   0.2595   0.07791   0.07105  -0.1402   0.9273   0.6112
   0.750   0.2714   0.07932   0.07238  -0.1374   0.9201   0.6445
   1.000   0.2911   0.08056   0.07352  -0.1360   0.9093   0.6814
   1.250   0.2985   0.08111   0.07402  -0.1332   0.8992   0.7094
   1.500   0.3347   0.08329   0.07603  -0.1355   0.8912   0.7424
   1.750   0.3472   0.08371   0.07637  -0.1350   0.8781   0.7525
   2.000   0.3694   0.08524   0.07778  -0.1367   0.8669   0.7620
   2.250   0.4151   0.08828   0.08062  -0.1418   0.8575   0.7774
   2.500   0.4323   0.08930   0.08157  -0.1424   0.8433   0.7892
   2.750   0.4469   0.09056   0.08277  -0.1425   0.8298   0.7999
   3.000   0.4668   0.09240   0.08454  -0.1437   0.8177   0.8086
   3.250   0.5019   0.09528   0.08730  -0.1476   0.8064   0.8151
   3.500   0.5445   0.09842   0.09031  -0.1522   0.7921   0.8199
   3.750   0.5565   0.09978   0.09166  -0.1524   0.7772   0.8232
   4.000   0.5733   0.10173   0.09357  -0.1533   0.7622   0.8265
   4.250   0.5902   0.10396   0.09576  -0.1545   0.7479   0.8293
   4.500   0.6093   0.10642   0.09818  -0.1560   0.7338   0.8322
   4.750   0.6286   0.10888   0.10061  -0.1573   0.7204   0.8357
   5.000   0.6550   0.11175   0.10344  -0.1595   0.7089   0.8400
   5.250   0.6902   0.11478   0.10642  -0.1624   0.6950   0.8447
   5.500   0.4781   0.11465   0.10729  -0.1214   0.6538   0.8369
   5.750   0.5081   0.11809   0.11066  -0.1239   0.6464   0.8414
   6.000   0.5169   0.11991   0.11248  -0.1241   0.6333   0.8445
   6.250   0.5181   0.12197   0.11455  -0.1239   0.6232   0.8468
   6.500   0.5506   0.12543   0.11796  -0.1265   0.6156   0.8511
   6.750   0.5412   0.12675   0.11932  -0.1253   0.6065   0.8526
   7.000   0.5721   0.13015   0.12269  -0.1276   0.5992   0.8579
   7.250   0.5634   0.13128   0.12386  -0.1266   0.5902   0.8602
   7.500   0.5912   0.13451   0.12707  -0.1285   0.5830   0.8662
   7.750   0.5860   0.13597   0.12858  -0.1278   0.5773   0.8692
   8.000   0.5967   0.13785   0.13048  -0.1282   0.5693   0.8742
   8.250   0.6288   0.14228   0.13490  -0.1307   0.5654   0.8818
   8.500   0.6064   0.14126   0.13397  -0.1282   0.5572   0.8834
   8.750   0.6270   0.14399   0.13672  -0.1293   0.5509   0.8920
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