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GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 195 AIRFOIL (goe195-il)
Reynolds number: 100,000
Max Cl/Cd: 64.41 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe195-il-100000-n5.txt
Download as CSV file: xf-goe195-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 195 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3278   0.09476   0.08994  -0.0283   1.0000   0.0728
  -7.250  -0.3389   0.09341   0.08869  -0.0263   1.0000   0.0746
  -7.000  -0.3560   0.09241   0.08783  -0.0290   1.0000   0.0774
  -6.750  -0.3557   0.08957   0.08504  -0.0360   0.9990   0.0781
  -6.500  -0.3349   0.08396   0.07943  -0.0400   0.9946   0.0789
  -6.000  -0.2711   0.06596   0.06117  -0.0622   0.9820   0.0541
  -5.750  -0.2480   0.06344   0.05861  -0.0630   0.9768   0.0526
  -5.500  -0.2161   0.05845   0.05354  -0.0700   0.9708   0.0509
  -5.250  -0.1726   0.05070   0.04558  -0.0826   0.9645   0.0491
  -5.000  -0.1144   0.03885   0.03309  -0.1010   0.9596   0.0495
  -4.750  -0.0677   0.03207   0.02548  -0.1105   0.9538   0.0485
  -4.500  -0.0233   0.02824   0.02095  -0.1161   0.9497   0.0484
  -4.250   0.0141   0.02589   0.01810  -0.1191   0.9437   0.0487
  -4.000   0.0507   0.02429   0.01612  -0.1214   0.9379   0.0504
  -3.750   0.0901   0.02286   0.01431  -0.1239   0.9340   0.0518
  -3.500   0.1223   0.02172   0.01292  -0.1249   0.9263   0.0522
  -3.250   0.1579   0.02067   0.01168  -0.1263   0.9204   0.0527
  -3.000   0.1916   0.01982   0.01068  -0.1274   0.9137   0.0532
  -2.750   0.2239   0.01910   0.00989  -0.1281   0.9059   0.0539
  -2.500   0.2575   0.01832   0.00908  -0.1292   0.8990   0.0552
  -2.250   0.2891   0.01776   0.00850  -0.1298   0.8899   0.0577
  -2.000   0.3206   0.01731   0.00800  -0.1303   0.8805   0.0614
  -1.750   0.3542   0.01685   0.00744  -0.1312   0.8722   0.0644
  -1.500   0.3841   0.01645   0.00700  -0.1313   0.8609   0.0679
  -1.250   0.4152   0.01605   0.00658  -0.1317   0.8503   0.0750
  -1.000   0.4476   0.01548   0.00617  -0.1323   0.8400   0.1091
  -0.750   0.4777   0.01512   0.00621  -0.1326   0.8277   0.2397
  -0.500   0.5070   0.01508   0.00618  -0.1325   0.8146   0.2897
  -0.250   0.5366   0.01499   0.00603  -0.1324   0.8014   0.3171
   0.000   0.5662   0.01485   0.00589  -0.1324   0.7879   0.3401
   0.250   0.5956   0.01471   0.00578  -0.1323   0.7742   0.3689
   0.500   0.6245   0.01458   0.00573  -0.1322   0.7604   0.4071
   0.750   0.6532   0.01448   0.00568  -0.1320   0.7465   0.4412
   1.000   0.6814   0.01440   0.00566  -0.1316   0.7324   0.4837
   1.250   0.7084   0.01428   0.00569  -0.1312   0.7182   0.5565
   1.500   0.7300   0.01368   0.00566  -0.1293   0.7041   0.7554
   2.000   0.7865   0.01393   0.00573  -0.1289   0.6748   1.0000
   2.250   0.8134   0.01413   0.00582  -0.1285   0.6600   1.0000
   2.500   0.8399   0.01434   0.00593  -0.1279   0.6441   1.0000
   2.750   0.8661   0.01454   0.00603  -0.1274   0.6282   1.0000
   3.000   0.8924   0.01476   0.00617  -0.1268   0.6136   1.0000
   3.250   0.9188   0.01499   0.00635  -0.1264   0.6007   1.0000
   3.500   0.9452   0.01524   0.00654  -0.1259   0.5893   1.0000
   3.750   0.9716   0.01551   0.00675  -0.1254   0.5787   1.0000
   4.000   0.9977   0.01580   0.00705  -0.1249   0.5676   1.0000
   4.250   1.0235   0.01610   0.00732  -0.1244   0.5557   1.0000
   4.500   1.0489   0.01643   0.00761  -0.1237   0.5424   1.0000
   4.750   1.0738   0.01679   0.00794  -0.1230   0.5277   1.0000
   5.000   1.0983   0.01715   0.00828  -0.1222   0.5121   1.0000
   5.250   1.1224   0.01751   0.00865  -0.1213   0.4962   1.0000
   5.500   1.1463   0.01787   0.00905  -0.1205   0.4801   1.0000
   5.750   1.1699   0.01820   0.00947  -0.1196   0.4630   1.0000
   6.000   1.1929   0.01853   0.00988  -0.1186   0.4437   1.0000
   6.250   1.2148   0.01886   0.01024  -0.1174   0.4194   1.0000
   6.500   1.2357   0.01924   0.01062  -0.1161   0.3880   1.0000
   6.750   1.2555   0.01974   0.01105  -0.1147   0.3541   1.0000
   7.000   1.2746   0.02036   0.01158  -0.1132   0.3225   1.0000
   7.250   1.2928   0.02111   0.01222  -0.1116   0.2921   1.0000
   7.500   1.3093   0.02201   0.01299  -0.1099   0.2596   1.0000
   7.750   1.3249   0.02300   0.01387  -0.1081   0.2280   1.0000
   8.000   1.3406   0.02397   0.01479  -0.1063   0.2000   1.0000
   8.250   1.3547   0.02504   0.01577  -0.1044   0.1689   1.0000
   8.500   1.3666   0.02628   0.01686  -0.1023   0.1393   1.0000
   8.750   1.3771   0.02761   0.01808  -0.1000   0.1160   1.0000
   9.000   1.3858   0.02904   0.01946  -0.0975   0.0970   1.0000
   9.250   1.3941   0.03039   0.02082  -0.0948   0.0795   1.0000
   9.500   1.4007   0.03178   0.02221  -0.0920   0.0663   1.0000
   9.750   1.4061   0.03329   0.02372  -0.0892   0.0582   1.0000
  10.000   1.4112   0.03485   0.02533  -0.0865   0.0525   1.0000
  10.250   1.4137   0.03664   0.02714  -0.0838   0.0488   1.0000
  10.500   1.4167   0.03847   0.02913  -0.0814   0.0459   1.0000
  10.750   1.4179   0.04052   0.03129  -0.0791   0.0435   1.0000
  11.000   1.4159   0.04294   0.03378  -0.0768   0.0415   1.0000
  11.250   1.4153   0.04538   0.03635  -0.0749   0.0397   1.0000
  11.500   1.4162   0.04778   0.03892  -0.0732   0.0380   1.0000
  11.750   1.4163   0.05037   0.04166  -0.0717   0.0365   1.0000
  12.000   1.4159   0.05309   0.04450  -0.0703   0.0353   1.0000
  12.250   1.4148   0.05597   0.04747  -0.0692   0.0340   1.0000
  12.500   1.4129   0.05902   0.05056  -0.0679   0.0328   1.0000
  12.750   1.4142   0.06185   0.05356  -0.0668   0.0317   1.0000
  13.000   1.4156   0.06474   0.05667  -0.0660   0.0305   1.0000
  13.250   1.4162   0.06777   0.05990  -0.0653   0.0295   1.0000
  13.500   1.4165   0.07092   0.06323  -0.0646   0.0287   1.0000
  13.750   1.4159   0.07422   0.06670  -0.0641   0.0279   1.0000
  14.000   1.4139   0.07772   0.07035  -0.0638   0.0272   1.0000
  14.250   1.4111   0.08133   0.07410  -0.0638   0.0264   1.0000
  14.500   1.4086   0.08499   0.07785  -0.0638   0.0257   1.0000
  14.750   1.4057   0.08891   0.08185  -0.0636   0.0250   1.0000
  15.000   1.3949   0.09401   0.08724  -0.0651   0.0247   1.0000
  15.250   1.3830   0.09954   0.09306  -0.0671   0.0243   1.0000
  15.500   1.3706   0.10544   0.09925  -0.0694   0.0241   1.0000
  15.750   1.3570   0.11178   0.10585  -0.0723   0.0238   1.0000
  16.000   1.3421   0.11864   0.11295  -0.0758   0.0237   1.0000
  16.250   1.3261   0.12612   0.12065  -0.0800   0.0236   1.0000
  16.500   1.3086   0.13439   0.12915  -0.0850   0.0236   1.0000
  16.750   1.2895   0.14366   0.13864  -0.0911   0.0237   1.0000
  17.000   1.2683   0.15426   0.14944  -0.0984   0.0238   1.0000
  17.250   1.2444   0.16670   0.16206  -0.1070   0.0241   1.0000
  17.500   1.2175   0.18166   0.17713  -0.1172   0.0245   1.0000
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