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LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il)
Reynolds number: 100,000
Max Cl/Cd: 55.37 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-l188tip-il-100000.txt
Download as CSV file: xf-l188tip-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED L-188 TIP 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4728   0.09639   0.09163  -0.0346   1.0000   0.1331
  -8.250  -0.5103   0.09456   0.08993  -0.0334   1.0000   0.1340
  -8.000  -0.5492   0.09148   0.08693  -0.0346   1.0000   0.1346
  -7.750  -0.5914   0.08840   0.08373  -0.0364   1.0000   0.1353
  -7.500  -0.5369   0.08580   0.08134  -0.0277   1.0000   0.1406
  -7.250  -0.5462   0.08298   0.07855  -0.0267   1.0000   0.1441
  -7.000  -0.6032   0.07921   0.07439  -0.0332   1.0000   0.1511
  -6.750  -0.5829   0.07461   0.07009  -0.0293   1.0000   0.1536
  -6.500  -0.5754   0.07233   0.06786  -0.0266   1.0000   0.1572
  -6.250  -0.5894   0.06804   0.06329  -0.0294   1.0000   0.1685
  -6.000  -0.5782   0.06534   0.06071  -0.0267   1.0000   0.1717
  -5.750  -0.5685   0.04660   0.03985  -0.0348   1.0000   0.0904
  -5.500  -0.5514   0.04288   0.03590  -0.0346   1.0000   0.0893
  -5.250  -0.5322   0.03946   0.03212  -0.0343   1.0000   0.0880
  -5.000  -0.5109   0.03630   0.02853  -0.0340   1.0000   0.0864
  -4.750  -0.4884   0.03382   0.02557  -0.0336   1.0000   0.0868
  -4.500  -0.4654   0.03215   0.02340  -0.0331   1.0000   0.0896
  -4.250  -0.4417   0.03045   0.02127  -0.0326   1.0000   0.0917
  -4.000  -0.4187   0.02889   0.01965  -0.0324   1.0000   0.0951
  -3.750  -0.3873   0.02807   0.01867  -0.0335   0.9978   0.1016
  -3.500  -0.3463   0.02689   0.01729  -0.0362   0.9942   0.1084
  -3.250  -0.3098   0.02633   0.01661  -0.0382   0.9893   0.1188
  -3.000  -0.2707   0.02556   0.01591  -0.0408   0.9853   0.1316
  -2.750  -0.2344   0.02498   0.01539  -0.0428   0.9806   0.1489
  -2.500  -0.1995   0.02434   0.01497  -0.0447   0.9758   0.1742
  -2.250  -0.1595   0.02365   0.01465  -0.0475   0.9721   0.2318
  -2.000  -0.1326   0.02165   0.01497  -0.0473   0.9691   0.6772
  -1.750  -0.1137   0.02174   0.01532  -0.0442   0.9626   0.7999
  -1.500  -0.0867   0.02198   0.01570  -0.0424   0.9579   0.8875
  -1.250  -0.0397   0.02225   0.01591  -0.0461   0.9512   1.0000
  -1.000  -0.0038   0.02258   0.01601  -0.0488   0.9450   1.0000
  -0.750   0.0283   0.02297   0.01618  -0.0507   0.9386   1.0000
  -0.500   0.0587   0.02331   0.01635  -0.0522   0.9314   1.0000
  -0.250   0.1011   0.02381   0.01668  -0.0558   0.9269   1.0000
   0.000   0.1208   0.02414   0.01690  -0.0552   0.9181   1.0000
   0.250   0.1589   0.02459   0.01722  -0.0578   0.9126   1.0000
   0.500   0.1845   0.02504   0.01758  -0.0581   0.9052   1.0000
   0.750   0.2161   0.02545   0.01791  -0.0595   0.8984   1.0000
   1.000   0.2597   0.02593   0.01831  -0.0629   0.8943   1.0000
   1.250   0.2736   0.02637   0.01870  -0.0611   0.8842   1.0000
   1.500   0.3149   0.02676   0.01905  -0.0640   0.8793   1.0000
   1.750   0.3325   0.02725   0.01951  -0.0628   0.8695   1.0000
   2.000   0.3735   0.02754   0.01979  -0.0654   0.8639   1.0000
   2.250   0.3933   0.02801   0.02024  -0.0646   0.8536   1.0000
   2.500   0.4365   0.02815   0.02039  -0.0673   0.8478   1.0000
   2.750   0.4569   0.02854   0.02080  -0.0664   0.8366   1.0000
   3.000   0.5079   0.02829   0.02059  -0.0699   0.8311   1.0000
   3.250   0.5318   0.02838   0.02071  -0.0691   0.8183   1.0000
   3.500   0.5639   0.02816   0.02054  -0.0693   0.8061   1.0000
   3.750   0.6082   0.02738   0.01983  -0.0709   0.7958   1.0000
   4.000   0.6603   0.02606   0.01863  -0.0733   0.7868   1.0000
   4.500   0.7395   0.02396   0.01674  -0.0742   0.7648   1.0000
   4.750   0.7892   0.02219   0.01508  -0.0756   0.7555   1.0000
   5.000   0.8243   0.02108   0.01410  -0.0751   0.7411   1.0000
   5.250   0.8623   0.01983   0.01295  -0.0749   0.7249   1.0000
   5.500   0.8950   0.01887   0.01207  -0.0740   0.7038   1.0000
   5.750   0.9253   0.01806   0.01132  -0.0727   0.6762   1.0000
   6.000   0.9470   0.01769   0.01096  -0.0703   0.6389   1.0000
   6.250   0.9668   0.01746   0.01062  -0.0675   0.5831   1.0000
   6.500   0.9783   0.01776   0.01046  -0.0634   0.4807   1.0000
   6.750   0.9756   0.01922   0.01096  -0.0577   0.3566   1.0000
   7.000   0.9755   0.02091   0.01199  -0.0532   0.2840   1.0000
   7.250   0.9821   0.02238   0.01304  -0.0498   0.2397   1.0000
   7.500   0.9930   0.02370   0.01408  -0.0472   0.2095   1.0000
   7.750   1.0082   0.02507   0.01516  -0.0454   0.1873   1.0000
   8.000   1.0267   0.02628   0.01630  -0.0441   0.1686   1.0000
   8.250   1.0484   0.02758   0.01750  -0.0433   0.1534   1.0000
   8.500   1.0736   0.02900   0.01879  -0.0431   0.1405   1.0000
   8.750   1.0974   0.03028   0.02005  -0.0427   0.1298   1.0000
   9.000   1.1223   0.03175   0.02164  -0.0424   0.1207   1.0000
   9.250   1.1531   0.03360   0.02336  -0.0433   0.1127   1.0000
   9.500   1.1731   0.03495   0.02498  -0.0421   0.1062   1.0000
   9.750   1.2061   0.03731   0.02718  -0.0435   0.1001   1.0000
  10.000   1.2210   0.03882   0.02910  -0.0414   0.0957   1.0000
  10.250   1.2407   0.04054   0.03097  -0.0404   0.0913   1.0000
  10.500   1.2691   0.04365   0.03405  -0.0413   0.0875   1.0000
  10.750   1.2744   0.04554   0.03645  -0.0380   0.0852   1.0000
  11.000   1.2812   0.04781   0.03911  -0.0353   0.0825   1.0000
  11.250   1.2895   0.05032   0.04190  -0.0330   0.0804   1.0000
  11.500   1.3006   0.05285   0.04461  -0.0313   0.0785   1.0000
  11.750   1.3145   0.05585   0.04768  -0.0305   0.0765   1.0000
  12.000   1.3106   0.05977   0.05190  -0.0275   0.0753   1.0000
  12.250   1.2941   0.06246   0.05498  -0.0226   0.0748   1.0000
  12.500   1.2747   0.06552   0.05837  -0.0180   0.0745   1.0000
  12.750   1.2535   0.06901   0.06217  -0.0141   0.0743   1.0000
  13.000   1.2308   0.07294   0.06637  -0.0110   0.0743   1.0000
  13.250   1.2070   0.07734   0.07102  -0.0087   0.0745   1.0000
  13.500   1.1825   0.08225   0.07615  -0.0073   0.0748   1.0000
  13.750   1.1580   0.08769   0.08178  -0.0068   0.0751   1.0000
  14.000   1.1359   0.09370   0.08794  -0.0072   0.0755   1.0000
  14.250   0.7486   0.12483   0.11983  -0.0142   0.1006   1.0000
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