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GOE 801 (MVA 301) AIRFOIL (goe801-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 801 (MVA 301) AIRFOIL (goe801-il)
Reynolds number: 50,000
Max Cl/Cd: 17.92 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe801-il-50000.txt
Download as CSV file: xf-goe801-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 801 (MVA 301) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2549   0.12519   0.11818  -0.0344   1.0000   0.1223
  -9.500  -0.2640   0.12537   0.11848  -0.0347   1.0000   0.1250
  -9.250  -0.2809   0.12672   0.11999  -0.0344   1.0000   0.1259
  -9.000  -0.2658   0.12040   0.11371  -0.0330   1.0000   0.1286
  -8.750  -0.2583   0.11689   0.11024  -0.0312   1.0000   0.1327
  -8.500  -0.2621   0.11533   0.10876  -0.0296   1.0000   0.1362
  -8.250  -0.2724   0.11464   0.10819  -0.0278   1.0000   0.1392
  -8.000  -0.2905   0.11502   0.10870  -0.0255   1.0000   0.1411
  -7.750  -0.3138   0.11591   0.10974  -0.0227   1.0000   0.1419
  -7.500  -0.3363   0.11681   0.11079  -0.0213   1.0000   0.1425
  -7.250  -0.3295   0.11191   0.10595  -0.0187   1.0000   0.1447
  -7.000  -0.3218   0.10822   0.10229  -0.0159   1.0000   0.1491
  -6.750  -0.3294   0.10678   0.10094  -0.0140   1.0000   0.1526
  -6.500  -0.3405   0.10592   0.10017  -0.0133   1.0000   0.1562
  -6.250  -0.3554   0.10638   0.10072  -0.0158   1.0000   0.1589
  -6.000  -0.3580   0.10361   0.09804  -0.0154   1.0000   0.1608
  -5.750  -0.3533   0.09984   0.09431  -0.0108   1.0000   0.1654
  -5.500  -0.3551   0.09806   0.09259  -0.0105   1.0000   0.1714
  -5.250  -0.3563   0.09779   0.09234  -0.0178   1.0000   0.1768
  -5.000  -0.3554   0.09361   0.08825  -0.0114   1.0000   0.1811
  -4.750  -0.3520   0.09180   0.08646  -0.0124   1.0000   0.1898
  -4.250  -0.3432   0.08686   0.08160  -0.0128   1.0000   0.2030
  -4.000  -0.3328   0.08458   0.07931  -0.0166   1.0000   0.2121
  -3.750  -0.3160   0.08316   0.07782  -0.0220   1.0000   0.2262
  -3.500  -0.3161   0.07974   0.07451  -0.0173   1.0000   0.2312
  -3.250  -0.3021   0.07753   0.07228  -0.0200   1.0000   0.2453
  -3.000  -0.2885   0.07536   0.07010  -0.0219   1.0000   0.2609
  -2.750  -0.2595   0.07231   0.06705  -0.0247   0.9934   0.2831
  -2.500  -0.2167   0.06929   0.06396  -0.0316   0.9822   0.3260
  -1.750  -0.1592   0.06133   0.05623  -0.0267   0.9495   0.4954
  -1.500  -0.1427   0.05890   0.05389  -0.0226   0.9397   0.5693
  -1.250  -0.1337   0.05662   0.05169  -0.0183   0.9279   0.6229
  -1.000  -0.1202   0.05425   0.04939  -0.0146   0.9166   0.6677
  -0.750  -0.0885   0.05181   0.04694  -0.0160   0.9056   0.7074
  -0.500   0.2159   0.05067   0.04347  -0.0968   0.8814   0.3384
  -0.250   0.2963   0.04898   0.04053  -0.1065   0.8690   0.2073
   0.000   0.3617   0.04732   0.03809  -0.1123   0.8590   0.1758
   0.250   0.3937   0.04640   0.03703  -0.1135   0.8454   0.1694
   0.500   0.4290   0.04588   0.03619  -0.1148   0.8322   0.1657
   0.750   0.4664   0.04543   0.03544  -0.1163   0.8197   0.1639
   1.000   0.5203   0.04446   0.03406  -0.1194   0.8104   0.1617
   1.250   0.5470   0.04451   0.03391  -0.1191   0.7965   0.1625
   1.500   0.5737   0.04464   0.03393  -0.1188   0.7833   0.1652
   1.750   0.6033   0.04475   0.03395  -0.1189   0.7709   0.1725
   2.000   0.6548   0.04379   0.03296  -0.1212   0.7625   0.1923
   2.250   0.6748   0.04434   0.03362  -0.1204   0.7488   0.2115
   2.500   0.6992   0.04450   0.03431  -0.1205   0.7361   0.3005
   2.750   0.7212   0.04387   0.03444  -0.1185   0.7252   1.0000
   3.000   0.7605   0.04397   0.03413  -0.1192   0.7158   1.0000
   3.250   0.7717   0.04562   0.03564  -0.1177   0.7024   1.0000
   3.500   0.7863   0.04715   0.03704  -0.1166   0.6902   1.0000
   3.750   0.8345   0.04656   0.03627  -0.1179   0.6832   1.0000
   4.000   0.8347   0.04912   0.03880  -0.1159   0.6699   1.0000
   4.250   0.8404   0.05143   0.04108  -0.1144   0.6580   1.0000
   4.500   0.8885   0.05070   0.04024  -0.1154   0.6514   1.0000
   4.750   0.8776   0.05439   0.04395  -0.1132   0.6386   1.0000
   5.000   0.8809   0.05711   0.04665  -0.1119   0.6281   1.0000
   5.250   0.9201   0.05697   0.04649  -0.1121   0.6203   1.0000
   5.500   0.9043   0.06130   0.05084  -0.1103   0.6087   1.0000
   5.750   0.9240   0.06272   0.05226  -0.1096   0.5991   1.0000
   6.000   0.9496   0.06349   0.05304  -0.1089   0.5889   1.0000
   6.250   0.9418   0.06713   0.05669  -0.1073   0.5767   1.0000
   6.500   0.9570   0.06875   0.05833  -0.1063   0.5654   1.0000
   6.750   1.0141   0.06627   0.05591  -0.1057   0.5554   1.0000
   7.500   1.0130   0.07562   0.06538  -0.1018   0.5186   1.0000
   7.750   1.0551   0.07426   0.06412  -0.1004   0.5075   1.0000
   8.000   1.0367   0.07940   0.06930  -0.0993   0.4937   1.0000
   8.250   1.0296   0.08344   0.07340  -0.0984   0.4807   1.0000
   8.500   1.0377   0.08586   0.07588  -0.0972   0.4680   1.0000
   8.750   1.0757   0.08474   0.07487  -0.0954   0.4562   1.0000
   9.000   1.0882   0.08657   0.07679  -0.0942   0.4437   1.0000
   9.250   1.0600   0.09355   0.08379  -0.0942   0.4303   1.0000
   9.500   1.0477   0.09872   0.08901  -0.0940   0.4184   1.0000
  11.500   1.0671   0.12915   0.11999  -0.0930   0.3476   1.0000
  11.750   1.0388   0.13776   0.12862  -0.0960   0.3464   1.0000
  12.000   1.0201   0.14468   0.13558  -0.0985   0.3449   1.0000
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