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LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il)
Reynolds number: 200,000
Max Cl/Cd: 72.58 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-l7769-il-200000.txt
Download as CSV file: xf-l7769-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LISSAMAN 7769 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4057   0.11413   0.10940   0.0144   0.5854   0.0574
  -9.250  -0.4109   0.11154   0.10684   0.0101   0.5838   0.0596
  -9.000  -0.4274   0.10923   0.10459   0.0037   0.5828   0.0601
  -8.750  -0.4174   0.10428   0.09963   0.0035   0.5803   0.0606
  -8.500  -0.3967   0.10068   0.09595   0.0054   0.5774   0.0614
  -8.250  -0.3823   0.09792   0.09317   0.0058   0.5748   0.0626
  -8.000  -0.3736   0.09514   0.09043   0.0049   0.5721   0.0640
  -7.750  -0.3681   0.09228   0.08759   0.0034   0.5695   0.0658
  -7.500  -0.3683   0.08936   0.08470   0.0009   0.5673   0.0680
  -7.250  -0.3915   0.08582   0.08116  -0.0131   0.5669   0.0698
  -7.000  -0.3840   0.08066   0.07599  -0.0145   0.5647   0.0704
  -6.750  -0.3694   0.07771   0.07303  -0.0121   0.5621   0.0710
  -6.500  -0.3552   0.07522   0.07050  -0.0112   0.5599   0.0720
  -6.250  -0.3414   0.07250   0.06780  -0.0120   0.5576   0.0732
  -6.000  -0.3275   0.06950   0.06479  -0.0141   0.5551   0.0751
  -5.750  -0.3121   0.06588   0.06110  -0.0185   0.5529   0.0786
  -5.500  -0.2963   0.06000   0.05493  -0.0260   0.5512   0.0821
  -5.250  -0.2789   0.05770   0.05265  -0.0253   0.5487   0.0832
  -5.000  -0.2600   0.05543   0.05033  -0.0255   0.5465   0.0848
  -4.750  -0.2394   0.05291   0.04769  -0.0266   0.5445   0.0874
  -4.500  -0.2124   0.04866   0.04284  -0.0313   0.5427   0.0943
  -4.250  -0.1916   0.04587   0.04014  -0.0315   0.5398   0.0953
  -4.000  -0.1664   0.03488   0.02809  -0.0339   0.5383   0.0705
  -3.750  -0.1420   0.03347   0.02671  -0.0341   0.5357   0.0717
  -3.500  -0.1165   0.02973   0.02256  -0.0341   0.5335   0.0665
  -3.250  -0.0908   0.02529   0.01738  -0.0339   0.5316   0.0636
  -3.000  -0.0637   0.02348   0.01518  -0.0335   0.5297   0.0639
  -2.750  -0.0364   0.02239   0.01382  -0.0332   0.5279   0.0649
  -2.500  -0.0086   0.02168   0.01294  -0.0330   0.5259   0.0669
  -2.250   0.0199   0.02112   0.01223  -0.0329   0.5232   0.0694
  -2.000   0.0476   0.02030   0.01139  -0.0327   0.5203   0.0719
  -1.750   0.0754   0.01993   0.01104  -0.0325   0.5177   0.0751
  -1.500   0.1033   0.01957   0.01060  -0.0322   0.5156   0.0798
  -1.250   0.1308   0.01923   0.01029  -0.0319   0.5138   0.0866
  -1.000   0.1584   0.01914   0.01021  -0.0316   0.5121   0.0989
  -0.750   0.1862   0.01931   0.01035  -0.0314   0.5105   0.1173
  -0.500   0.2144   0.01949   0.01061  -0.0315   0.5082   0.1327
  -0.250   0.2422   0.01961   0.01082  -0.0316   0.5055   0.1450
   0.000   0.2699   0.01966   0.01090  -0.0316   0.5027   0.1564
   0.250   0.2975   0.01974   0.01099  -0.0315   0.5004   0.1698
   0.500   0.3249   0.01977   0.01105  -0.0314   0.4986   0.1833
   0.750   0.3518   0.01962   0.01100  -0.0312   0.4970   0.1942
   1.000   0.3788   0.01958   0.01099  -0.0309   0.4956   0.2051
   1.250   0.4056   0.01966   0.01110  -0.0307   0.4942   0.2191
   1.500   0.4324   0.01992   0.01157  -0.0309   0.4914   0.2371
   2.000   0.5012   0.01869   0.01248  -0.0339   0.4856   1.0000
   2.250   0.5278   0.01911   0.01281  -0.0337   0.4835   1.0000
   2.500   0.5545   0.01938   0.01299  -0.0334   0.4816   1.0000
   2.750   0.5813   0.01957   0.01308  -0.0329   0.4800   1.0000
   3.000   0.6080   0.01986   0.01328  -0.0325   0.4785   1.0000
   3.250   0.6341   0.02039   0.01377  -0.0323   0.4769   1.0000
   3.500   0.6589   0.02158   0.01516  -0.0331   0.4715   1.0000
   3.750   0.6852   0.02190   0.01547  -0.0329   0.4679   1.0000
   4.000   0.7125   0.02173   0.01523  -0.0322   0.4653   1.0000
   4.250   0.7403   0.02149   0.01487  -0.0315   0.4632   1.0000
   4.500   0.7675   0.02147   0.01476  -0.0308   0.4614   1.0000
   4.750   0.7905   0.02286   0.01640  -0.0316   0.4551   1.0000
   5.000   0.8166   0.02319   0.01676  -0.0314   0.4517   1.0000
   5.250   0.8439   0.02315   0.01669  -0.0309   0.4494   1.0000
   5.500   0.8718   0.02296   0.01644  -0.0303   0.4476   1.0000
   5.750   0.8997   0.02281   0.01623  -0.0297   0.4459   1.0000
   6.000   0.9211   0.02419   0.01787  -0.0302   0.4388   1.0000
   6.250   0.9485   0.02401   0.01769  -0.0297   0.4352   1.0000
   6.500   0.9781   0.02326   0.01686  -0.0289   0.4326   1.0000
   6.750   1.0084   0.02240   0.01590  -0.0281   0.4303   1.0000
   7.000   1.0314   0.02309   0.01679  -0.0281   0.4233   1.0000
   7.250   1.0592   0.02282   0.01653  -0.0277   0.4194   1.0000
   7.500   1.0885   0.02224   0.01593  -0.0271   0.4167   1.0000
   7.750   1.1185   0.02161   0.01520  -0.0265   0.4143   1.0000
   8.000   1.1410   0.02219   0.01605  -0.0264   0.4064   1.0000
   8.250   1.1698   0.02170   0.01555  -0.0259   0.4025   1.0000
   8.500   1.2001   0.02100   0.01479  -0.0254   0.3995   1.0000
   8.750   1.2237   0.02126   0.01528  -0.0252   0.3912   1.0000
   9.000   1.2531   0.02056   0.01456  -0.0246   0.3861   1.0000
   9.250   1.2789   0.02041   0.01456  -0.0243   0.3780   1.0000
   9.500   1.3081   0.01959   0.01370  -0.0237   0.3699   1.0000
   9.750   1.3337   0.01928   0.01351  -0.0233   0.3568   1.0000
  10.000   1.3594   0.01900   0.01329  -0.0229   0.3413   1.0000
  10.250   1.3833   0.01906   0.01342  -0.0226   0.3206   1.0000
  10.500   1.4050   0.01936   0.01365  -0.0221   0.2932   1.0000
  10.750   1.4221   0.02023   0.01437  -0.0215   0.2645   1.0000
  11.000   1.4351   0.02156   0.01558  -0.0209   0.2413   1.0000
  11.250   1.4448   0.02313   0.01708  -0.0202   0.2235   1.0000
  11.500   1.4510   0.02493   0.01886  -0.0195   0.2087   1.0000
  11.750   1.4518   0.02712   0.02109  -0.0191   0.1965   1.0000
  12.000   1.4426   0.03040   0.02445  -0.0196   0.1877   1.0000
  12.250   1.4324   0.03388   0.02791  -0.0201   0.1798   1.0000
  12.500   1.4259   0.03703   0.03111  -0.0204   0.1707   1.0000
  12.750   1.4176   0.04032   0.03442  -0.0207   0.1621   1.0000
  13.000   1.4085   0.04371   0.03780  -0.0210   0.1537   1.0000
  13.250   1.4008   0.04707   0.04120  -0.0214   0.1440   1.0000
  13.500   1.3906   0.05073   0.04485  -0.0219   0.1341   1.0000
  13.750   1.3792   0.05460   0.04869  -0.0225   0.1242   1.0000
  14.000   1.3665   0.05884   0.05289  -0.0235   0.1122   1.0000
  14.250   1.3543   0.06336   0.05739  -0.0246   0.0963   1.0000
  14.500   1.3381   0.06859   0.06251  -0.0262   0.0791   1.0000
  14.750   1.3223   0.07392   0.06772  -0.0278   0.0663   1.0000
  15.000   1.3084   0.07915   0.07287  -0.0293   0.0578   1.0000
  15.250   1.3013   0.08351   0.07725  -0.0306   0.0525   1.0000
  15.500   1.2911   0.08840   0.08209  -0.0321   0.0490   1.0000
  15.750   1.2884   0.09229   0.08606  -0.0333   0.0458   1.0000
  16.000   1.2841   0.09643   0.09022  -0.0346   0.0436   1.0000
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