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GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il)
Reynolds number: 100,000
Max Cl/Cd: 45.4 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe344-il-100000.txt
Download as CSV file: xf-goe344-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 344 (PFALZ 71) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4892   0.10227   0.09703  -0.0079   1.0000   0.0999
  -8.250  -0.5044   0.10046   0.09534  -0.0122   1.0000   0.1022
  -8.000  -0.5186   0.09870   0.09357  -0.0218   1.0000   0.1032
  -7.750  -0.5016   0.09227   0.08722  -0.0148   1.0000   0.1049
  -7.500  -0.4905   0.08878   0.08372  -0.0125   1.0000   0.1076
  -7.250  -0.4852   0.08560   0.08056  -0.0132   1.0000   0.1111
  -7.000  -0.4886   0.08352   0.07834  -0.0248   1.0000   0.1173
  -6.750  -0.4808   0.07815   0.07306  -0.0218   1.0000   0.1188
  -6.500  -0.4700   0.07501   0.06998  -0.0180   1.0000   0.1224
  -6.250  -0.4601   0.07197   0.06690  -0.0197   1.0000   0.1291
  -6.000  -0.4503   0.06775   0.06255  -0.0238   1.0000   0.1339
  -5.750  -0.4393   0.06458   0.05943  -0.0215   1.0000   0.1368
  -5.500  -0.4209   0.06166   0.05614  -0.0269   1.0000   0.1477
  -5.250  -0.4107   0.05782   0.05246  -0.0240   1.0000   0.1500
  -4.750  -0.3796   0.05194   0.04641  -0.0238   1.0000   0.1659
  -4.500  -0.3592   0.04932   0.04353  -0.0252   1.0000   0.1785
  -4.250  -0.3443   0.04633   0.04060  -0.0236   1.0000   0.1820
  -4.000  -0.3041   0.03625   0.02916  -0.0284   1.0000   0.1163
  -3.750  -0.2836   0.03307   0.02585  -0.0278   1.0000   0.1127
  -3.500  -0.2562   0.02809   0.01977  -0.0273   1.0000   0.1026
  -3.250  -0.2320   0.02581   0.01708  -0.0266   1.0000   0.1028
  -3.000  -0.2086   0.02410   0.01528  -0.0259   1.0000   0.1062
  -2.750  -0.1846   0.02306   0.01413  -0.0252   1.0000   0.1108
  -2.500  -0.1585   0.02166   0.01238  -0.0244   1.0000   0.1145
  -2.250  -0.1323   0.02038   0.01085  -0.0238   1.0000   0.1196
  -2.000  -0.1072   0.01967   0.01010  -0.0232   1.0000   0.1291
  -1.750  -0.0819   0.01893   0.00935  -0.0226   1.0000   0.1431
  -1.500  -0.0557   0.01813   0.00847  -0.0220   1.0000   0.1625
  -1.250  -0.0302   0.01747   0.00800  -0.0218   1.0000   0.1874
  -1.000  -0.0049   0.01705   0.00772  -0.0214   1.0000   0.2141
  -0.750   0.0199   0.01678   0.00758  -0.0210   1.0000   0.2425
  -0.500   0.0449   0.01653   0.00744  -0.0206   1.0000   0.2704
  -0.250   0.0702   0.01625   0.00734  -0.0202   1.0000   0.2999
   0.000   0.0958   0.01595   0.00730  -0.0200   1.0000   0.3430
   0.250   0.1351   0.01399   0.00720  -0.0217   1.0000   1.0000
   0.500   0.1552   0.01433   0.00734  -0.0207   1.0000   1.0000
   0.750   0.1791   0.01473   0.00764  -0.0207   0.9982   1.0000
   1.000   0.2429   0.01488   0.00768  -0.0283   0.9838   1.0000
   1.250   0.3010   0.01476   0.00752  -0.0345   0.9641   1.0000
   1.500   0.3610   0.01447   0.00725  -0.0407   0.9455   1.0000
   1.750   0.4160   0.01401   0.00683  -0.0455   0.9219   1.0000
   2.000   0.4676   0.01351   0.00637  -0.0493   0.8929   1.0000
   2.250   0.5126   0.01308   0.00596  -0.0515   0.8495   1.0000
   2.500   0.5509   0.01282   0.00558  -0.0521   0.7879   1.0000
   2.750   0.5839   0.01292   0.00535  -0.0517   0.7184   1.0000
   3.000   0.6084   0.01340   0.00548  -0.0501   0.6519   1.0000
   3.250   0.6307   0.01397   0.00569  -0.0484   0.5946   1.0000
   3.500   0.6531   0.01455   0.00598  -0.0468   0.5474   1.0000
   3.750   0.6760   0.01512   0.00636  -0.0456   0.5093   1.0000
   4.000   0.6994   0.01568   0.00675  -0.0445   0.4789   1.0000
   4.250   0.7231   0.01622   0.00715  -0.0435   0.4533   1.0000
   4.500   0.7467   0.01672   0.00755  -0.0425   0.4292   1.0000
   4.750   0.7698   0.01719   0.00796  -0.0414   0.4049   1.0000
   5.000   0.7929   0.01769   0.00833  -0.0404   0.3822   1.0000
   5.250   0.8161   0.01819   0.00882  -0.0394   0.3603   1.0000
   5.500   0.8393   0.01874   0.00934  -0.0384   0.3399   1.0000
   5.750   0.8624   0.01935   0.00985  -0.0375   0.3200   1.0000
   6.000   0.8848   0.01986   0.01046  -0.0364   0.2974   1.0000
   6.250   0.9065   0.02042   0.01093  -0.0353   0.2740   1.0000
   6.500   0.9272   0.02090   0.01148  -0.0339   0.2454   1.0000
   6.750   0.9466   0.02150   0.01205  -0.0323   0.2116   1.0000
   7.000   0.9662   0.02237   0.01283  -0.0307   0.1797   1.0000
   7.250   0.9862   0.02341   0.01370  -0.0294   0.1576   1.0000
   7.500   1.0071   0.02457   0.01487  -0.0281   0.1406   1.0000
   7.750   1.0283   0.02588   0.01613  -0.0270   0.1278   1.0000
   8.000   1.0494   0.02719   0.01741  -0.0259   0.1164   1.0000
   8.250   1.0702   0.02857   0.01899  -0.0246   0.1065   1.0000
   8.500   1.0908   0.03035   0.02086  -0.0235   0.0981   1.0000
   8.750   1.1115   0.03211   0.02256  -0.0226   0.0900   1.0000
   9.000   1.1296   0.03423   0.02509  -0.0209   0.0839   1.0000
   9.250   1.1488   0.03623   0.02706  -0.0200   0.0777   1.0000
   9.500   1.1623   0.03905   0.03037  -0.0179   0.0736   1.0000
   9.750   1.1745   0.04177   0.03352  -0.0158   0.0701   1.0000
  10.000   1.1890   0.04405   0.03589  -0.0144   0.0664   1.0000
  10.250   1.1956   0.04812   0.04024  -0.0126   0.0638   1.0000
  10.500   1.1933   0.05147   0.04419  -0.0093   0.0627   1.0000
  10.750   1.1865   0.05546   0.04869  -0.0062   0.0621   1.0000
  11.000   1.1741   0.05969   0.05333  -0.0031   0.0619   1.0000
  11.250   1.1559   0.06392   0.05790  -0.0001   0.0619   1.0000
  11.500   1.1322   0.06796   0.06218   0.0029   0.0622   1.0000
  11.750   1.1071   0.07266   0.06709   0.0040   0.0625   1.0000
  12.000   1.0812   0.07831   0.07292   0.0030   0.0630   1.0000
  12.250   1.0559   0.08511   0.07985  -0.0001   0.0636   1.0000
  12.500   1.0342   0.09279   0.08758  -0.0039   0.0642   1.0000
  12.750   0.9316   0.12478   0.11971  -0.0278   0.0771   1.0000
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