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GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 397 AIRFOIL (goe397-il)
Reynolds number: 50,000
Max Cl/Cd: 42.84 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe397-il-50000.txt
Download as CSV file: xf-goe397-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 397 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4127   0.10885   0.10186  -0.0140   1.0000   0.1179
  -8.250  -0.4184   0.10826   0.10139  -0.0164   1.0000   0.1204
  -8.000  -0.4261   0.10823   0.10150  -0.0203   1.0000   0.1211
  -7.750  -0.4011   0.09993   0.09315  -0.0160   1.0000   0.1297
  -7.500  -0.4060   0.09899   0.09233  -0.0188   1.0000   0.1339
  -7.250  -0.3968   0.09447   0.08786  -0.0180   1.0000   0.1393
  -7.000  -0.3930   0.09221   0.08562  -0.0200   1.0000   0.1467
  -6.750  -0.3870   0.08865   0.08215  -0.0206   1.0000   0.1526
  -6.500  -0.3818   0.08660   0.08014  -0.0235   1.0000   0.1614
  -6.250  -0.3736   0.08250   0.07611  -0.0224   1.0000   0.1680
  -6.000  -0.3674   0.08093   0.07458  -0.0279   1.0000   0.1772
  -5.750  -0.3590   0.07688   0.07059  -0.0250   1.0000   0.1880
  -5.500  -0.3513   0.07355   0.06732  -0.0247   1.0000   0.1974
  -5.250  -0.3436   0.07059   0.06441  -0.0252   1.0000   0.2103
  -5.000  -0.3357   0.06770   0.06157  -0.0252   1.0000   0.2253
  -4.750  -0.3268   0.06559   0.05946  -0.0275   1.0000   0.2479
  -4.500  -0.3232   0.06224   0.05622  -0.0232   1.0000   0.2686
  -4.250  -0.3192   0.05965   0.05370  -0.0211   1.0000   0.2971
  -4.000  -0.3156   0.05748   0.05154  -0.0198   1.0000   0.3330
  -3.500  -0.3179   0.05220   0.04649  -0.0097   1.0000   0.4085
  -3.250  -0.3241   0.04990   0.04432  -0.0031   1.0000   0.4618
  -3.000  -0.3296   0.04780   0.04232   0.0033   1.0000   0.5159
  -2.750  -0.3351   0.04525   0.03990   0.0107   1.0000   0.5600
  -2.500  -0.3388   0.04283   0.03760   0.0173   1.0000   0.6031
  -2.250  -0.3401   0.04055   0.03539   0.0226   1.0000   0.6440
  -2.000  -0.3413   0.03813   0.03306   0.0289   1.0000   0.6815
  -1.750  -0.3323   0.03572   0.03068   0.0309   1.0000   0.7082
  -1.500  -0.0617   0.03278   0.02429  -0.0426   1.0000   0.2292
  -1.250  -0.0301   0.03115   0.02209  -0.0435   1.0000   0.2006
  -1.000  -0.0025   0.02989   0.02035  -0.0437   1.0000   0.1881
  -0.750   0.0239   0.02880   0.01878  -0.0435   1.0000   0.1750
  -0.500   0.0486   0.02771   0.01742  -0.0433   1.0000   0.1683
  -0.250   0.0727   0.02721   0.01639  -0.0427   1.0000   0.1626
   0.000   0.0948   0.02651   0.01550  -0.0421   1.0000   0.1615
   0.250   0.1183   0.02605   0.01480  -0.0418   1.0000   0.1615
   0.500   0.1438   0.02569   0.01423  -0.0418   1.0000   0.1643
   0.750   0.1678   0.02549   0.01392  -0.0418   1.0000   0.1762
   1.000   0.1917   0.02527   0.01369  -0.0418   1.0000   0.1875
   1.250   0.2150   0.02518   0.01361  -0.0417   1.0000   0.1999
   1.500   0.2409   0.02514   0.01368  -0.0423   0.9992   0.2264
   1.750   0.2956   0.02367   0.01353  -0.0476   0.9873   1.0000
   2.000   0.3431   0.02475   0.01427  -0.0525   0.9729   1.0000
   2.250   0.3885   0.02577   0.01512  -0.0570   0.9581   1.0000
   2.500   0.4335   0.02673   0.01602  -0.0613   0.9429   1.0000
   2.750   0.4786   0.02765   0.01693  -0.0654   0.9275   1.0000
   3.000   0.5155   0.02848   0.01783  -0.0680   0.9106   1.0000
   3.250   0.5523   0.02931   0.01874  -0.0705   0.8934   1.0000
   3.500   0.5918   0.03013   0.01968  -0.0732   0.8759   1.0000
   3.750   0.6345   0.03089   0.02067  -0.0762   0.8589   1.0000
   4.000   0.6739   0.03164   0.02162  -0.0785   0.8416   1.0000
   4.250   0.7021   0.03256   0.02274  -0.0791   0.8228   1.0000
   4.500   0.7386   0.03334   0.02378  -0.0807   0.8052   1.0000
   4.750   0.7769   0.03403   0.02485  -0.0823   0.7885   1.0000
   5.000   0.8337   0.03235   0.02364  -0.0821   0.7558   1.0000
   5.250   0.8937   0.02661   0.01833  -0.0747   0.6942   1.0000
   5.500   0.9216   0.02359   0.01559  -0.0672   0.6358   1.0000
   5.750   0.9270   0.02164   0.01351  -0.0572   0.4929   1.0000
   6.000   0.9180   0.02461   0.01405  -0.0497   0.2301   1.0000
   6.250   0.9283   0.02743   0.01615  -0.0470   0.1775   1.0000
   6.500   0.9491   0.03015   0.01848  -0.0453   0.1466   1.0000
   6.750   0.9803   0.03285   0.02114  -0.0445   0.1263   1.0000
   7.000   1.0123   0.03593   0.02433  -0.0440   0.1147   1.0000
   7.250   1.0411   0.03905   0.02774  -0.0432   0.1086   1.0000
   7.500   1.0639   0.04255   0.03154  -0.0422   0.1025   1.0000
   7.750   1.0832   0.04593   0.03551  -0.0405   0.1003   1.0000
   8.000   1.1009   0.04998   0.04008  -0.0388   0.1011   1.0000
   8.250   1.1156   0.05446   0.04501  -0.0372   0.1029   1.0000
   8.500   1.1323   0.05983   0.05062  -0.0363   0.1051   1.0000
   8.750   1.1216   0.06349   0.05544  -0.0330   0.1117   1.0000
   9.000   1.1225   0.06874   0.06105  -0.0317   0.1155   1.0000
   9.250   1.1364   0.07503   0.06736  -0.0314   0.1182   1.0000
   9.500   1.0936   0.07966   0.07277  -0.0299   0.1283   1.0000
   9.750   1.0640   0.08522   0.07858  -0.0301   0.1363   1.0000
  10.000   1.0286   0.09127   0.08468  -0.0321   0.1399   1.0000
  10.250   1.0040   0.09920   0.09265  -0.0369   0.1485   1.0000
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