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LOCKHEED L-188 TIP AIRFOIL (l188tip-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED L-188 TIP AIRFOIL (l188tip-il)
Reynolds number: 50,000
Max Cl/Cd: 33.41 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-l188tip-il-50000-n5.txt
Download as CSV file: xf-l188tip-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4370   0.10373   0.09623  -0.0489   1.0000   0.0651
  -9.750  -0.4444   0.10016   0.09274  -0.0491   1.0000   0.0649
  -9.500  -0.4539   0.09659   0.08925  -0.0491   1.0000   0.0646
  -9.250  -0.4659   0.09302   0.08577  -0.0490   1.0000   0.0642
  -9.000  -0.4813   0.08939   0.08223  -0.0488   1.0000   0.0637
  -8.750  -0.5020   0.08567   0.07860  -0.0485   1.0000   0.0631
  -8.500  -0.5263   0.08211   0.07513  -0.0476   1.0000   0.0625
  -8.250  -0.5464   0.07817   0.07119  -0.0468   1.0000   0.0619
  -8.000  -0.5645   0.07410   0.06708  -0.0459   1.0000   0.0615
  -7.750  -0.5794   0.06991   0.06278  -0.0450   1.0000   0.0610
  -7.500  -0.5902   0.06566   0.05835  -0.0440   1.0000   0.0608
  -7.250  -0.5963   0.06145   0.05390  -0.0431   1.0000   0.0607
  -7.000  -0.5974   0.05740   0.04953  -0.0421   1.0000   0.0608
  -6.750  -0.5938   0.05374   0.04553  -0.0412   1.0000   0.0617
  -6.500  -0.5865   0.05026   0.04161  -0.0403   1.0000   0.0633
  -6.250  -0.5761   0.04675   0.03752  -0.0396   1.0000   0.0651
  -6.000  -0.5618   0.04353   0.03370  -0.0388   1.0000   0.0666
  -5.750  -0.5449   0.04139   0.03138  -0.0381   1.0000   0.0680
  -5.500  -0.5246   0.03974   0.02954  -0.0378   0.9994   0.0707
  -5.250  -0.4936   0.03771   0.02705  -0.0393   0.9957   0.0751
  -5.000  -0.4617   0.03559   0.02437  -0.0406   0.9923   0.0786
  -4.750  -0.4315   0.03433   0.02305  -0.0418   0.9884   0.0834
  -4.500  -0.3981   0.03305   0.02140  -0.0432   0.9848   0.0897
  -4.250  -0.3673   0.03192   0.02022  -0.0442   0.9809   0.0956
  -4.000  -0.3360   0.03106   0.01910  -0.0449   0.9767   0.1042
  -3.750  -0.3037   0.03023   0.01832  -0.0462   0.9730   0.1138
  -3.500  -0.2726   0.02952   0.01754  -0.0471   0.9689   0.1258
  -3.250  -0.2428   0.02888   0.01686  -0.0478   0.9640   0.1417
  -3.000  -0.2102   0.02827   0.01624  -0.0492   0.9598   0.1651
  -2.750  -0.1778   0.02756   0.01572  -0.0508   0.9558   0.2019
  -2.500  -0.1505   0.02660   0.01522  -0.0517   0.9505   0.2761
  -2.250  -0.1269   0.02524   0.01542  -0.0510   0.9466   0.5530
  -2.000  -0.1023   0.02520   0.01576  -0.0490   0.9423   0.7196
  -1.750  -0.0855   0.02519   0.01584  -0.0458   0.9355   0.8012
  -1.500  -0.0522   0.02528   0.01599  -0.0455   0.9309   0.8893
  -1.250   0.0163   0.02559   0.01609  -0.0534   0.9285   1.0000
  -1.000   0.0386   0.02572   0.01598  -0.0535   0.9210   1.0000
  -0.750   0.0667   0.02593   0.01596  -0.0545   0.9144   1.0000
  -0.500   0.0990   0.02620   0.01601  -0.0561   0.9091   1.0000
  -0.250   0.1202   0.02646   0.01609  -0.0557   0.9010   1.0000
   0.000   0.1540   0.02677   0.01623  -0.0575   0.8958   1.0000
   0.250   0.1761   0.02709   0.01642  -0.0571   0.8881   1.0000
   0.500   0.2060   0.02742   0.01662  -0.0581   0.8819   1.0000
   0.750   0.2360   0.02777   0.01687  -0.0591   0.8761   1.0000
   1.000   0.2586   0.02815   0.01716  -0.0587   0.8681   1.0000
   1.250   0.2933   0.02848   0.01742  -0.0604   0.8632   1.0000
   1.500   0.3119   0.02893   0.01782  -0.0594   0.8543   1.0000
   1.750   0.3443   0.02927   0.01812  -0.0606   0.8486   1.0000
   2.000   0.3657   0.02973   0.01856  -0.0601   0.8403   1.0000
   2.250   0.3958   0.03009   0.01891  -0.0609   0.8337   1.0000
   2.500   0.4194   0.03054   0.01936  -0.0606   0.8256   1.0000
   2.750   0.4489   0.03087   0.01972  -0.0612   0.8183   1.0000
   3.000   0.4721   0.03129   0.02016  -0.0608   0.8090   1.0000
   3.250   0.5055   0.03147   0.02041  -0.0618   0.8018   1.0000
   3.500   0.5269   0.03186   0.02085  -0.0609   0.7907   1.0000
   3.750   0.5583   0.03195   0.02102  -0.0614   0.7817   1.0000
   4.000   0.5902   0.03189   0.02106  -0.0617   0.7712   1.0000
   4.250   0.6162   0.03187   0.02113  -0.0610   0.7578   1.0000
   4.500   0.6452   0.03159   0.02096  -0.0604   0.7437   1.0000
   4.750   0.6761   0.03107   0.02059  -0.0598   0.7289   1.0000
   5.000   0.7073   0.03040   0.02004  -0.0589   0.7133   1.0000
   5.250   0.7384   0.02965   0.01944  -0.0580   0.6963   1.0000
   5.500   0.7706   0.02880   0.01875  -0.0570   0.6777   1.0000
   5.750   0.7945   0.02831   0.01840  -0.0551   0.6550   1.0000
   6.000   0.8213   0.02765   0.01785  -0.0534   0.6289   1.0000
   6.250   0.8435   0.02726   0.01757  -0.0511   0.5962   1.0000
   6.500   0.8611   0.02716   0.01752  -0.0484   0.5540   1.0000
   6.750   0.8834   0.02691   0.01715  -0.0461   0.4939   1.0000
   7.000   0.9038   0.02705   0.01679  -0.0435   0.4086   1.0000
   7.250   0.9121   0.02819   0.01738  -0.0403   0.3388   1.0000
   7.500   0.9177   0.02967   0.01846  -0.0373   0.2886   1.0000
   7.750   0.9249   0.03119   0.01968  -0.0347   0.2520   1.0000
   8.000   0.9342   0.03266   0.02096  -0.0326   0.2231   1.0000
   8.250   0.9451   0.03411   0.02224  -0.0307   0.2009   1.0000
   8.500   0.9587   0.03546   0.02356  -0.0291   0.1815   1.0000
   8.750   0.9740   0.03679   0.02484  -0.0277   0.1656   1.0000
   9.000   0.9911   0.03809   0.02611  -0.0265   0.1519   1.0000
   9.250   1.0105   0.03936   0.02735  -0.0255   0.1402   1.0000
   9.500   1.0319   0.04061   0.02865  -0.0248   0.1295   1.0000
   9.750   1.0559   0.04192   0.03010  -0.0243   0.1198   1.0000
  10.000   1.0796   0.04333   0.03148  -0.0239   0.1121   1.0000
  10.250   1.1015   0.04486   0.03324  -0.0233   0.1046   1.0000
  10.500   1.1258   0.04653   0.03491  -0.0231   0.0989   1.0000
  10.750   1.1434   0.04842   0.03712  -0.0221   0.0932   1.0000
  11.000   1.1626   0.05020   0.03893  -0.0215   0.0890   1.0000
  11.250   1.1781   0.05253   0.04154  -0.0205   0.0852   1.0000
  11.500   1.1856   0.05493   0.04430  -0.0187   0.0816   1.0000
  11.750   1.1940   0.05717   0.04672  -0.0172   0.0787   1.0000
  12.000   1.2063   0.05941   0.04902  -0.0162   0.0763   1.0000
  12.250   1.2050   0.06249   0.05241  -0.0142   0.0745   1.0000
  12.500   1.1944   0.06596   0.05631  -0.0118   0.0730   1.0000
  12.750   1.1817   0.06964   0.06033  -0.0097   0.0716   1.0000
  13.000   1.1671   0.07358   0.06457  -0.0082   0.0705   1.0000
  13.250   1.1500   0.07792   0.06919  -0.0072   0.0696   1.0000
  13.500   1.1291   0.08292   0.07445  -0.0070   0.0690   1.0000
  13.750   1.1015   0.08908   0.08088  -0.0078   0.0689   1.0000
  14.000   1.0626   0.09748   0.08956  -0.0107   0.0694   1.0000
  14.250   1.0100   0.10998   0.10228  -0.0174   0.0708   1.0000
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