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GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il)
Reynolds number: 200,000
Max Cl/Cd: 79.34 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe331-il-200000.txt
Download as CSV file: xf-goe331-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 331 (PFALZ 60) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.0612   0.09161   0.08815  -0.0776   0.9610   0.0304
  -8.000  -0.0389   0.08792   0.08444  -0.0828   0.9571   0.0311
  -7.750  -0.0258   0.08504   0.08155  -0.0858   0.9470   0.0318
  -7.500  -0.0095   0.08210   0.07859  -0.0911   0.9389   0.0325
  -7.250   0.0102   0.07946   0.07589  -0.1026   0.9267   0.0329
  -7.000   0.0211   0.07610   0.07254  -0.1018   0.9190   0.0331
  -6.750   0.0344   0.07293   0.06938  -0.1009   0.9133   0.0335
  -6.500   0.0504   0.07011   0.06653  -0.1028   0.9070   0.0342
  -6.250   0.0659   0.06747   0.06387  -0.1052   0.8986   0.0351
  -6.000   0.0874   0.06446   0.06080  -0.1091   0.8932   0.0360
  -5.750   0.1098   0.06180   0.05806  -0.1140   0.8840   0.0372
  -5.500   0.1454   0.05831   0.05435  -0.1225   0.8784   0.0379
  -5.250   0.1558   0.05571   0.05179  -0.1211   0.8702   0.0383
  -5.000   0.1752   0.05306   0.04909  -0.1220   0.8643   0.0390
  -4.750   0.1965   0.05069   0.04665  -0.1236   0.8565   0.0400
  -4.500   0.2233   0.04817   0.04399  -0.1262   0.8494   0.0418
  -4.250   0.2596   0.04545   0.04098  -0.1308   0.8426   0.0438
  -4.000   0.2771   0.04316   0.03869  -0.1307   0.8350   0.0446
  -3.750   0.3029   0.04099   0.03639  -0.1320   0.8296   0.0461
  -3.500   0.3289   0.03921   0.03448  -0.1331   0.8213   0.0484
  -3.250   0.3634   0.03707   0.03201  -0.1353   0.8151   0.0508
  -3.000   0.3841   0.03511   0.03005  -0.1354   0.8080   0.0521
  -2.750   0.4096   0.03353   0.02835  -0.1358   0.8006   0.0547
  -2.500   0.4445   0.03201   0.02642  -0.1371   0.7951   0.0591
  -2.250   0.4649   0.03031   0.02477  -0.1369   0.7863   0.0609
  -2.000   0.4986   0.02968   0.02368  -0.1373   0.7798   0.0685
  -1.750   0.5196   0.02764   0.02174  -0.1374   0.7718   0.0708
  -1.500   0.5519   0.02764   0.02130  -0.1372   0.7642   0.0795
  -1.250   0.5746   0.02526   0.01901  -0.1375   0.7569   0.0824
  -1.000   0.6033   0.02474   0.01822  -0.1374   0.7492   0.0931
  -0.750   0.6294   0.02317   0.01665  -0.1377   0.7430   0.0992
  -0.500   0.6548   0.02224   0.01563  -0.1375   0.7345   0.1121
  -0.250   0.6828   0.02133   0.01458  -0.1377   0.7281   0.1303
   0.000   0.7070   0.02043   0.01365  -0.1375   0.7191   0.1588
   0.250   0.7341   0.01999   0.01307  -0.1374   0.7117   0.2012
   0.500   0.7570   0.01840   0.01159  -0.1373   0.7023   0.2417
   0.750   0.7841   0.01743   0.01057  -0.1371   0.6946   0.2803
   1.000   0.8120   0.01702   0.01004  -0.1365   0.6846   0.2857
   1.250   0.8472   0.01686   0.00942  -0.1357   0.6765   0.1981
   1.500   0.8788   0.01656   0.00872  -0.1337   0.6658   0.1007
   1.750   0.9068   0.01630   0.00819  -0.1326   0.6551   0.0796
   2.000   0.9334   0.01560   0.00746  -0.1320   0.6440   0.0744
   2.250   0.9587   0.01525   0.00704  -0.1311   0.6303   0.0702
   2.500   0.9835   0.01495   0.00675  -0.1303   0.6156   0.0716
   2.750   1.0082   0.01474   0.00650  -0.1295   0.5996   0.0711
   3.000   1.0323   0.01460   0.00630  -0.1286   0.5816   0.0703
   3.250   1.0556   0.01456   0.00617  -0.1276   0.5608   0.0705
   3.500   1.0778   0.01465   0.00612  -0.1264   0.5360   0.0717
   3.750   1.0990   0.01487   0.00615  -0.1250   0.5090   0.0742
   4.000   1.1191   0.01522   0.00628  -0.1235   0.4818   0.0791
   4.250   1.1395   0.01554   0.00649  -0.1221   0.4568   0.0973
   4.500   1.1575   0.01459   0.00686  -0.1204   0.4379   1.0000
   4.750   1.1785   0.01507   0.00714  -0.1192   0.4222   1.0000
   5.000   1.2000   0.01555   0.00745  -0.1181   0.4098   1.0000
   5.250   1.2215   0.01607   0.00778  -0.1171   0.4000   1.0000
   5.500   1.2441   0.01649   0.00815  -0.1164   0.3909   1.0000
   5.750   1.2667   0.01703   0.00854  -0.1156   0.3835   1.0000
   6.000   1.2895   0.01745   0.00895  -0.1149   0.3762   1.0000
   6.250   1.3130   0.01798   0.00937  -0.1144   0.3701   1.0000
   6.500   1.3369   0.01847   0.00984  -0.1140   0.3649   1.0000
   6.750   1.3603   0.01892   0.01031  -0.1134   0.3597   1.0000
   7.000   1.3848   0.01944   0.01077  -0.1131   0.3551   1.0000
   7.250   1.4109   0.02004   0.01131  -0.1132   0.3509   1.0000
   7.500   1.4333   0.02049   0.01185  -0.1125   0.3465   1.0000
   7.750   1.4565   0.02098   0.01237  -0.1120   0.3420   1.0000
   8.000   1.4818   0.02155   0.01289  -0.1119   0.3378   1.0000
   8.250   1.5064   0.02217   0.01354  -0.1118   0.3336   1.0000
   8.500   1.5263   0.02263   0.01412  -0.1107   0.3290   1.0000
   8.750   1.5480   0.02313   0.01464  -0.1100   0.3241   1.0000
   9.000   1.5760   0.02385   0.01526  -0.1105   0.3195   1.0000
   9.250   1.5943   0.02437   0.01596  -0.1092   0.3160   1.0000
   9.500   1.6144   0.02492   0.01664  -0.1083   0.3124   1.0000
   9.750   1.6363   0.02549   0.01728  -0.1077   0.3089   1.0000
  10.000   1.6609   0.02610   0.01793  -0.1076   0.3055   1.0000
  10.250   1.6858   0.02688   0.01873  -0.1077   0.3015   1.0000
  10.500   1.6968   0.02738   0.01944  -0.1052   0.2971   1.0000
  10.750   1.7107   0.02783   0.01997  -0.1033   0.2918   1.0000
  11.000   1.7329   0.02843   0.02050  -0.1029   0.2858   1.0000
  11.250   1.7322   0.02892   0.02123  -0.0985   0.2812   1.0000
  11.500   1.7384   0.02943   0.02184  -0.0954   0.2758   1.0000
  11.750   1.7562   0.02997   0.02230  -0.0944   0.2700   1.0000
  12.000   1.7529   0.03076   0.02335  -0.0902   0.2655   1.0000
  12.250   1.7564   0.03151   0.02423  -0.0873   0.2600   1.0000
  12.500   1.7680   0.03217   0.02485  -0.0855   0.2546   1.0000
  12.750   1.7659   0.03334   0.02628  -0.0823   0.2495   1.0000
  13.000   1.7677   0.03443   0.02751  -0.0799   0.2438   1.0000
  13.250   1.7720   0.03557   0.02868  -0.0778   0.2379   1.0000
  13.500   1.7705   0.03715   0.03050  -0.0756   0.2312   1.0000
  13.750   1.7721   0.03864   0.03202  -0.0737   0.2249   1.0000
  14.000   1.7719   0.04049   0.03411  -0.0721   0.2172   1.0000
  14.250   1.7705   0.04247   0.03612  -0.0705   0.2097   1.0000
  14.500   1.7692   0.04470   0.03856  -0.0692   0.1995   1.0000
  14.750   1.7658   0.04727   0.04124  -0.0681   0.1877   1.0000
  15.000   1.7583   0.05042   0.04444  -0.0670   0.1722   1.0000
  15.250   1.7443   0.05445   0.04845  -0.0661   0.1526   1.0000
  15.500   1.7232   0.05953   0.05345  -0.0653   0.1327   1.0000
  15.750   1.6986   0.06533   0.05919  -0.0648   0.1161   1.0000
  16.000   1.6728   0.07162   0.06546  -0.0649   0.0994   1.0000
  16.250   1.6455   0.07845   0.07228  -0.0654   0.0836   1.0000
  16.500   1.6178   0.08560   0.07945  -0.0664   0.0713   1.0000
  16.750   1.5908   0.09297   0.08685  -0.0678   0.0641   1.0000
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