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GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il)
Reynolds number: 1,000,000
Max Cl/Cd: 147.3 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe332-il-1000000.txt
Download as CSV file: xf-goe332-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 332 (PFALZ 61) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.0162   0.08528   0.08334  -0.0874   0.8867   0.0217
  -9.750  -0.1284   0.09698   0.09525  -0.0749   0.9766   0.0203
  -9.500  -0.1131   0.09379   0.09206  -0.0781   0.9660   0.0208
  -9.250  -0.0973   0.08797   0.08618  -0.0869   0.9410   0.0228
  -9.000  -0.0875   0.08353   0.08150  -0.0914   0.8864   0.0229
  -8.750  -0.0829   0.08034   0.07813  -0.0930   0.8538   0.0229
  -8.500  -0.0813   0.07653   0.07424  -0.0941   0.8353   0.0232
  -8.250  -0.0713   0.07453   0.07217  -0.0945   0.8213   0.0233
  -8.000  -0.0608   0.07247   0.07006  -0.0953   0.8093   0.0235
  -7.750  -0.0510   0.07041   0.06796  -0.0965   0.7986   0.0238
  -7.000   0.0271   0.04340   0.04084  -0.1101   0.7457   0.0271
  -6.750   0.0329   0.03587   0.03321  -0.1180   0.7389   0.0273
  -6.500   0.0472   0.03306   0.03037  -0.1199   0.7309   0.0276
  -6.250   0.0643   0.03072   0.02795  -0.1217   0.7225   0.0278
  -6.000   0.0833   0.02858   0.02577  -0.1235   0.7145   0.0282
  -5.750   0.1029   0.02625   0.02335  -0.1256   0.7066   0.0288
  -5.500   0.1206   0.01256   0.00895  -0.1374   0.7048   0.0324
  -5.250   0.1431   0.01143   0.00777  -0.1378   0.6971   0.0327
  -4.750   0.1901   0.00966   0.00579  -0.1384   0.6828   0.0334
  -4.500   0.2170   0.01634   0.01138  -0.1449   0.6889   0.0310
  -4.250   0.2430   0.01450   0.00923  -0.1450   0.6820   0.0304
  -4.000   0.2695   0.01335   0.00783  -0.1449   0.6748   0.0302
  -3.750   0.2968   0.01249   0.00678  -0.1449   0.6684   0.0301
  -3.500   0.3242   0.01185   0.00598  -0.1448   0.6613   0.0303
  -3.250   0.3516   0.01135   0.00536  -0.1447   0.6545   0.0305
  -3.000   0.3795   0.01102   0.00494  -0.1446   0.6478   0.0311
  -2.750   0.4070   0.01075   0.00456  -0.1445   0.6415   0.0314
  -2.500   0.4351   0.01047   0.00424  -0.1445   0.6365   0.0317
  -2.250   0.4632   0.01028   0.00399  -0.1445   0.6310   0.0320
  -2.000   0.4903   0.00969   0.00334  -0.1444   0.6258   0.0325
  -1.750   0.5181   0.00938   0.00301  -0.1444   0.6212   0.0330
  -1.500   0.5463   0.00917   0.00279  -0.1445   0.6165   0.0336
  -1.250   0.5741   0.00904   0.00264  -0.1444   0.6115   0.0342
  -1.000   0.6019   0.00894   0.00251  -0.1444   0.6066   0.0350
  -0.750   0.6303   0.00882   0.00239  -0.1445   0.6021   0.0360
  -0.500   0.6584   0.00875   0.00231  -0.1445   0.5973   0.0371
  -0.250   0.6861   0.00870   0.00221  -0.1444   0.5924   0.0380
   0.000   0.7144   0.00856   0.00207  -0.1445   0.5879   0.0399
   0.250   0.7426   0.00850   0.00202  -0.1446   0.5826   0.0420
   0.500   0.7702   0.00850   0.00198  -0.1445   0.5775   0.0442
   0.750   0.7982   0.00844   0.00194  -0.1445   0.5728   0.0521
   1.000   0.8264   0.00828   0.00200  -0.1447   0.5677   0.1256
   1.250   0.8540   0.00830   0.00204  -0.1447   0.5619   0.1438
   1.500   0.8816   0.00832   0.00207  -0.1447   0.5563   0.1584
   1.750   0.9095   0.00830   0.00210  -0.1447   0.5502   0.1790
   2.000   0.9366   0.00799   0.00224  -0.1449   0.5441   0.3929
   2.250   0.9583   0.00686   0.00244  -0.1437   0.5385   1.0000
   2.500   0.9857   0.00695   0.00248  -0.1437   0.5317   1.0000
   2.750   1.0126   0.00706   0.00254  -0.1435   0.5246   1.0000
   3.000   1.0398   0.00716   0.00260  -0.1434   0.5159   1.0000
   3.250   1.0664   0.00729   0.00268  -0.1432   0.5062   1.0000
   3.500   1.0923   0.00746   0.00277  -0.1429   0.4941   1.0000
   3.750   1.1185   0.00761   0.00287  -0.1426   0.4816   1.0000
   4.000   1.1445   0.00777   0.00297  -0.1423   0.4700   1.0000
   4.250   1.1700   0.00796   0.00311  -0.1420   0.4574   1.0000
   4.500   1.1950   0.00818   0.00325  -0.1415   0.4433   1.0000
   4.750   1.2197   0.00842   0.00341  -0.1410   0.4298   1.0000
   5.000   1.2446   0.00864   0.00358  -0.1406   0.4175   1.0000
   5.250   1.2699   0.00884   0.00374  -0.1402   0.4075   1.0000
   5.500   1.2945   0.00907   0.00393  -0.1397   0.3977   1.0000
   5.750   1.3191   0.00929   0.00411  -0.1392   0.3880   1.0000
   6.000   1.3437   0.00950   0.00431  -0.1387   0.3793   1.0000
   6.250   1.3671   0.00978   0.00453  -0.1380   0.3688   1.0000
   6.500   1.3906   0.01005   0.00475  -0.1374   0.3565   1.0000
   6.750   1.4137   0.01032   0.00499  -0.1367   0.3449   1.0000
   7.000   1.4362   0.01062   0.00525  -0.1359   0.3343   1.0000
   7.250   1.4582   0.01093   0.00551  -0.1349   0.3233   1.0000
   7.500   1.4810   0.01119   0.00576  -0.1342   0.3145   1.0000
   7.750   1.5020   0.01152   0.00605  -0.1331   0.3048   1.0000
   8.000   1.5226   0.01185   0.00635  -0.1320   0.2932   1.0000
   8.250   1.5427   0.01216   0.00664  -0.1307   0.2831   1.0000
   8.500   1.5607   0.01253   0.00698  -0.1291   0.2724   1.0000
   8.750   1.5774   0.01296   0.00736  -0.1273   0.2592   1.0000
   9.000   1.5930   0.01347   0.00780  -0.1253   0.2426   1.0000
   9.250   1.6025   0.01426   0.00844  -0.1223   0.2161   1.0000
   9.500   1.6100   0.01517   0.00919  -0.1191   0.1892   1.0000
   9.750   1.6176   0.01611   0.01001  -0.1160   0.1674   1.0000
  10.000   1.6237   0.01715   0.01094  -0.1129   0.1474   1.0000
  10.250   1.6267   0.01840   0.01205  -0.1094   0.1219   1.0000
  10.500   1.6206   0.02027   0.01371  -0.1050   0.0893   1.0000
  10.750   1.6209   0.02190   0.01524  -0.1017   0.0726   1.0000
  11.000   1.6103   0.02441   0.01756  -0.0976   0.0390   1.0000
  11.250   1.6062   0.02667   0.01978  -0.0945   0.0253   1.0000
  11.500   1.6114   0.02833   0.02147  -0.0927   0.0220   1.0000
  11.750   1.6186   0.02987   0.02306  -0.0911   0.0203   1.0000
  12.000   1.6231   0.03169   0.02492  -0.0895   0.0188   1.0000
  12.250   1.6298   0.03337   0.02666  -0.0881   0.0180   1.0000
  12.500   1.6366   0.03508   0.02844  -0.0869   0.0173   1.0000
  12.750   1.6416   0.03697   0.03039  -0.0856   0.0166   1.0000
  13.000   1.6447   0.03910   0.03257  -0.0843   0.0160   1.0000
  13.250   1.6442   0.04165   0.03521  -0.0830   0.0153   1.0000
  13.500   1.6471   0.04392   0.03755  -0.0819   0.0148   1.0000
  13.750   1.6510   0.04613   0.03983  -0.0810   0.0145   1.0000
  14.000   1.6536   0.04852   0.04230  -0.0802   0.0141   1.0000
  14.250   1.6551   0.05108   0.04494  -0.0794   0.0137   1.0000
  14.500   1.6559   0.05380   0.04772  -0.0787   0.0134   1.0000
  14.750   1.6548   0.05675   0.05075  -0.0781   0.0131   1.0000
  15.000   1.6511   0.06006   0.05414  -0.0775   0.0127   1.0000
  15.250   1.6446   0.06381   0.05798  -0.0770   0.0125   1.0000
  15.500   1.6333   0.06824   0.06252  -0.0766   0.0122   1.0000
  15.750   1.6304   0.07166   0.06604  -0.0763   0.0120   1.0000
  16.000   1.6279   0.07507   0.06954  -0.0762   0.0119   1.0000
  16.250   1.6245   0.07867   0.07323  -0.0762   0.0117   1.0000
  16.500   1.6201   0.08245   0.07709  -0.0763   0.0115   1.0000
  16.750   1.6150   0.08636   0.08110  -0.0765   0.0113   1.0000
  17.000   1.6093   0.09037   0.08519  -0.0768   0.0112   1.0000
  17.250   1.6036   0.09444   0.08935  -0.0772   0.0110   1.0000
  17.500   1.5972   0.09869   0.09369  -0.0777   0.0108   1.0000
  17.750   1.5906   0.10301   0.09809  -0.0784   0.0106   1.0000
  18.000   1.5835   0.10742   0.10258  -0.0792   0.0105   1.0000
  18.250   1.5760   0.11192   0.10716  -0.0801   0.0103   1.0000
  18.500   1.5674   0.11664   0.11197  -0.0812   0.0102   1.0000
  18.750   1.5572   0.12166   0.11707  -0.0825   0.0100   1.0000
  19.000   1.5458   0.12694   0.12244  -0.0840   0.0099   1.0000
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