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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 100,000
Max Cl/Cd: 53.75 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe325-il-100000.txt
Download as CSV file: xf-goe325-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 325 (PFALZ 54) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3329   0.09216   0.08762  -0.0226   1.0000   0.0661
  -7.000  -0.3334   0.08976   0.08528  -0.0226   1.0000   0.0678
  -6.750  -0.3340   0.08739   0.08297  -0.0232   1.0000   0.0698
  -6.500  -0.3340   0.08519   0.08083  -0.0253   1.0000   0.0721
  -6.250  -0.3277   0.08413   0.07971  -0.0344   1.0000   0.0741
  -6.000  -0.3206   0.08058   0.07613  -0.0375   1.0000   0.0748
  -5.750  -0.3209   0.07596   0.07167  -0.0317   1.0000   0.0762
  -5.500  -0.3171   0.07307   0.06883  -0.0288   1.0000   0.0786
  -5.250  -0.3094   0.07040   0.06617  -0.0289   1.0000   0.0826
  -5.000  -0.2799   0.06798   0.06340  -0.0402   1.0000   0.0892
  -4.750  -0.2793   0.06373   0.05934  -0.0362   1.0000   0.0908
  -4.500  -0.2718   0.06096   0.05663  -0.0344   1.0000   0.0937
  -4.250  -0.2543   0.05833   0.05389  -0.0364   1.0000   0.1002
  -4.000  -0.2330   0.05484   0.05024  -0.0399   1.0000   0.1055
  -3.750  -0.2219   0.05235   0.04780  -0.0389   1.0000   0.1100
  -3.500  -0.1984   0.04958   0.04483  -0.0419   1.0000   0.1205
  -3.250  -0.1696   0.04706   0.04211  -0.0452   0.9983   0.1341
  -3.000  -0.1186   0.04307   0.03800  -0.0520   0.9895   0.1507
  -2.750  -0.0635   0.03977   0.03447  -0.0595   0.9799   0.1793
  -2.500  -0.0146   0.03689   0.03154  -0.0652   0.9709   0.2243
  -1.500   0.2211   0.02483   0.01713  -0.0868   0.9304   0.1231
  -1.250   0.2704   0.02282   0.01466  -0.0896   0.9172   0.1097
  -1.000   0.3153   0.02132   0.01271  -0.0913   0.9018   0.1049
  -0.750   0.3552   0.01984   0.01121  -0.0927   0.8845   0.1099
  -0.500   0.3878   0.01869   0.00994  -0.0923   0.8599   0.1114
  -0.250   0.4202   0.01765   0.00879  -0.0918   0.8341   0.1137
   0.000   0.4509   0.01682   0.00782  -0.0910   0.8058   0.1179
   0.250   0.4788   0.01595   0.00696  -0.0900   0.7762   0.1269
   0.500   0.5057   0.01547   0.00633  -0.0888   0.7465   0.1479
   0.750   0.5316   0.01290   0.00568  -0.0872   0.7201   1.0000
   1.000   0.5583   0.01316   0.00542  -0.0862   0.6932   1.0000
   1.250   0.5843   0.01346   0.00539  -0.0854   0.6674   1.0000
   1.500   0.6102   0.01378   0.00543  -0.0847   0.6431   1.0000
   1.750   0.6363   0.01412   0.00548  -0.0841   0.6218   1.0000
   2.000   0.6623   0.01449   0.00564  -0.0836   0.6005   1.0000
   2.250   0.6885   0.01490   0.00584  -0.0831   0.5816   1.0000
   2.500   0.7148   0.01535   0.00607  -0.0826   0.5643   1.0000
   2.750   0.7411   0.01584   0.00636  -0.0823   0.5484   1.0000
   3.000   0.7676   0.01634   0.00675  -0.0820   0.5338   1.0000
   3.250   0.7939   0.01685   0.00716  -0.0817   0.5200   1.0000
   3.500   0.8202   0.01736   0.00762  -0.0815   0.5072   1.0000
   3.750   0.8465   0.01789   0.00809  -0.0812   0.4956   1.0000
   4.000   0.8731   0.01842   0.00857  -0.0810   0.4858   1.0000
   4.250   0.8994   0.01894   0.00910  -0.0808   0.4760   1.0000
   4.500   0.9255   0.01950   0.00969  -0.0806   0.4670   1.0000
   4.750   0.9522   0.02001   0.01015  -0.0804   0.4591   1.0000
   5.000   0.9777   0.02058   0.01087  -0.0802   0.4503   1.0000
   5.250   1.0046   0.02114   0.01138  -0.0801   0.4440   1.0000
   5.500   1.0297   0.02180   0.01223  -0.0799   0.4365   1.0000
   5.750   1.0562   0.02237   0.01284  -0.0797   0.4305   1.0000
   6.000   1.0811   0.02308   0.01372  -0.0794   0.4237   1.0000
   6.250   1.1069   0.02371   0.01445  -0.0792   0.4176   1.0000
   6.500   1.1329   0.02445   0.01527  -0.0790   0.4128   1.0000
   6.750   1.1566   0.02532   0.01644  -0.0787   0.4067   1.0000
   7.000   1.1827   0.02598   0.01718  -0.0785   0.4016   1.0000
   7.250   1.2058   0.02676   0.01819  -0.0780   0.3944   1.0000
   7.500   1.2315   0.02674   0.01813  -0.0773   0.3836   1.0000
   7.750   1.2563   0.02653   0.01792  -0.0765   0.3703   1.0000
   8.000   1.2794   0.02635   0.01776  -0.0755   0.3559   1.0000
   8.250   1.3015   0.02623   0.01772  -0.0743   0.3412   1.0000
   8.500   1.3201   0.02600   0.01767  -0.0727   0.3229   1.0000
   8.750   1.3377   0.02555   0.01731  -0.0708   0.3009   1.0000
   9.000   1.3512   0.02514   0.01714  -0.0683   0.2720   1.0000
   9.250   1.3531   0.02557   0.01724  -0.0645   0.1515   1.0000
   9.500   1.3394   0.02959   0.02036  -0.0601   0.0753   1.0000
   9.750   1.3378   0.03211   0.02292  -0.0567   0.0637   1.0000
  10.000   1.3321   0.03443   0.02534  -0.0529   0.0590   1.0000
  10.250   1.3291   0.03649   0.02759  -0.0495   0.0557   1.0000
  10.500   1.3242   0.03882   0.03007  -0.0467   0.0531   1.0000
  10.750   1.3173   0.04152   0.03286  -0.0443   0.0510   1.0000
  11.000   1.3082   0.04463   0.03600  -0.0422   0.0493   1.0000
  11.250   1.3082   0.04718   0.03866  -0.0407   0.0473   1.0000
  11.500   1.3109   0.04961   0.04122  -0.0394   0.0453   1.0000
  11.750   1.3173   0.05180   0.04350  -0.0378   0.0437   1.0000
  12.000   1.3291   0.05370   0.04542  -0.0359   0.0423   1.0000
  12.250   1.3466   0.05553   0.04726  -0.0339   0.0410   1.0000
  12.500   1.3721   0.05766   0.04942  -0.0321   0.0400   1.0000
  12.750   1.4101   0.06194   0.05375  -0.0315   0.0386   1.0000
  13.000   1.4043   0.06489   0.05700  -0.0299   0.0383   1.0000
  13.250   1.3971   0.06822   0.06063  -0.0288   0.0380   1.0000
  13.500   1.3884   0.07196   0.06470  -0.0281   0.0377   1.0000
  13.750   1.3785   0.07615   0.06916  -0.0279   0.0377   1.0000
  14.000   1.3671   0.08075   0.07403  -0.0282   0.0377   1.0000
  14.250   1.3543   0.08578   0.07930  -0.0289   0.0379   1.0000
  14.500   1.3398   0.09119   0.08495  -0.0302   0.0381   1.0000
  14.750   1.3247   0.09697   0.09095  -0.0320   0.0383   1.0000
  15.000   1.3095   0.10315   0.09733  -0.0341   0.0385   1.0000
  15.250   1.2942   0.10920   0.10360  -0.0368   0.0388   1.0000
  15.500   1.2741   0.11540   0.11003  -0.0410   0.0391   1.0000
  15.750   1.2503   0.12297   0.11784  -0.0467   0.0395   1.0000
  16.000   1.2178   0.13343   0.12855  -0.0550   0.0402   1.0000
  16.250   1.1291   0.16243   0.15788  -0.0773   0.0462   1.0000
  16.500   1.1143   0.17276   0.16821  -0.0831   0.0477   1.0000
  16.750   1.1115   0.17944   0.17487  -0.0859   0.0486   1.0000
  17.000   0.8111   0.17402   0.16964  -0.0642   0.0580   1.0000
  17.250   0.8140   0.17744   0.17307  -0.0647   0.0594   1.0000
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