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LIEBECK LA5055 AIRFOIL (la5055-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: LIEBECK LA5055 AIRFOIL (la5055-il)
Reynolds number: 1,000,000
Max Cl/Cd: 83.51 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-la5055-il-1000000-n5.txt
Download as CSV file: xf-la5055-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LIEBECK LA5055 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2204   0.09922   0.09545  -0.0332   0.5136   0.0222
 -10.000  -0.2137   0.09635   0.09259  -0.0347   0.5131   0.0223
  -9.500  -0.5978   0.02377   0.01859  -0.0717   0.5162   0.0284
  -9.250  -0.5771   0.02236   0.01698  -0.0713   0.5155   0.0286
  -9.000  -0.5559   0.02097   0.01541  -0.0710   0.5147   0.0288
  -8.750  -0.5313   0.02023   0.01458  -0.0707   0.5139   0.0290
  -8.500  -0.5054   0.01973   0.01402  -0.0704   0.5130   0.0291
  -8.250  -0.4793   0.01925   0.01348  -0.0702   0.5122   0.0293
  -8.000  -0.4526   0.01883   0.01301  -0.0700   0.5115   0.0294
  -7.750  -0.4259   0.01842   0.01254  -0.0698   0.5107   0.0295
  -7.500  -0.3990   0.01802   0.01208  -0.0696   0.5101   0.0297
  -7.250  -0.3720   0.01760   0.01160  -0.0695   0.5094   0.0298
  -7.000  -0.3450   0.01717   0.01110  -0.0693   0.5089   0.0300
  -6.750  -0.3177   0.01675   0.01062  -0.0691   0.5083   0.0302
  -6.500  -0.2905   0.01631   0.01011  -0.0690   0.5077   0.0304
  -6.250  -0.2632   0.01587   0.00959  -0.0688   0.5070   0.0307
  -6.000  -0.2357   0.01547   0.00912  -0.0687   0.5062   0.0309
  -5.750  -0.2079   0.01510   0.00868  -0.0686   0.5053   0.0313
  -5.500  -0.1802   0.01474   0.00824  -0.0685   0.5044   0.0316
  -5.250  -0.1523   0.01434   0.00778  -0.0683   0.5041   0.0319
  -5.000  -0.1242   0.01396   0.00734  -0.0682   0.5038   0.0321
  -4.750  -0.0959   0.01362   0.00695  -0.0682   0.5034   0.0323
  -4.500  -0.0675   0.01332   0.00660  -0.0681   0.5028   0.0325
  -4.250  -0.0389   0.01304   0.00629  -0.0680   0.5019   0.0326
  -4.000  -0.0110   0.01258   0.00579  -0.0680   0.5009   0.0329
  -3.750   0.0174   0.01225   0.00545  -0.0679   0.5000   0.0332
  -3.500   0.0460   0.01202   0.00521  -0.0679   0.4993   0.0334
  -3.250   0.0748   0.01182   0.00501  -0.0679   0.4986   0.0337
  -3.000   0.1036   0.01163   0.00482  -0.0679   0.4978   0.0339
  -2.750   0.1325   0.01144   0.00462  -0.0679   0.4965   0.0342
  -2.500   0.1615   0.01125   0.00442  -0.0679   0.4948   0.0345
  -2.250   0.1905   0.01109   0.00424  -0.0679   0.4927   0.0349
  -2.000   0.2194   0.01092   0.00404  -0.0679   0.4909   0.0353
  -1.750   0.2483   0.01074   0.00384  -0.0679   0.4891   0.0356
  -1.500   0.2771   0.01059   0.00366  -0.0679   0.4874   0.0359
  -1.250   0.3061   0.01043   0.00351  -0.0680   0.4864   0.0362
  -1.000   0.3352   0.01028   0.00336  -0.0680   0.4852   0.0365
  -0.750   0.3643   0.01015   0.00324  -0.0681   0.4836   0.0367
  -0.500   0.3934   0.01003   0.00312  -0.0681   0.4819   0.0369
  -0.250   0.4224   0.00989   0.00298  -0.0682   0.4801   0.0372
   0.000   0.4513   0.00972   0.00282  -0.0682   0.4781   0.0377
   0.250   0.4804   0.00960   0.00271  -0.0683   0.4758   0.0381
   0.500   0.5095   0.00951   0.00262  -0.0684   0.4733   0.0386
   0.750   0.5386   0.00944   0.00256  -0.0685   0.4712   0.0393
   1.000   0.5678   0.00938   0.00252  -0.0686   0.4684   0.0399
   1.250   0.5970   0.00931   0.00245  -0.0687   0.4613   0.0404
   1.500   0.6256   0.00931   0.00237  -0.0688   0.4440   0.0409
   1.750   0.6536   0.00944   0.00241  -0.0688   0.4280   0.0414
   2.000   0.6818   0.00954   0.00247  -0.0689   0.4192   0.0418
   2.250   0.7097   0.00967   0.00257  -0.0689   0.4103   0.0425
   2.500   0.7383   0.00970   0.00261  -0.0690   0.4058   0.0435
   2.750   0.7667   0.00977   0.00268  -0.0691   0.4005   0.0446
   3.000   0.7946   0.00991   0.00281  -0.0692   0.3937   0.0458
   3.250   0.8229   0.00999   0.00289  -0.0692   0.3849   0.0471
   3.500   0.8445   0.01095   0.00358  -0.0688   0.3187   0.0499
   3.750   0.8701   0.01133   0.00393  -0.0687   0.3064   0.0549
   4.000   0.8969   0.01153   0.00416  -0.0687   0.2990   0.0687
   4.250   0.9228   0.01174   0.00446  -0.0686   0.2916   0.1187
   4.500   0.9491   0.01165   0.00466  -0.0686   0.2868   0.2628
   4.750   0.9737   0.01166   0.00500  -0.0684   0.2769   0.4290
   5.000   0.9936   0.01251   0.00569  -0.0679   0.2319   0.4514
   5.250   1.0148   0.01303   0.00623  -0.0674   0.2155   0.4830
   5.500   1.0288   0.01262   0.00673  -0.0653   0.2097   0.8462
   6.000   1.0989   0.01330   0.00763  -0.0694   0.1991   1.0000
   6.250   1.1220   0.01373   0.00805  -0.0691   0.1952   1.0000
   6.500   1.1428   0.01435   0.00864  -0.0686   0.1896   1.0000
   6.750   1.1627   0.01501   0.00930  -0.0682   0.1854   1.0000
   7.000   1.1834   0.01562   0.00992  -0.0678   0.1828   1.0000
   7.250   1.2000   0.01671   0.01103  -0.0676   0.1766   1.0000
   7.500   1.2021   0.01997   0.01434  -0.0686   0.1710   1.0000
   7.750   1.1756   0.02339   0.01784  -0.0652   0.1690   1.0000
   8.000   1.1479   0.02735   0.02172  -0.0626   0.1462   1.0000
   8.250   1.1371   0.03020   0.02451  -0.0611   0.1317   1.0000
   8.500   1.1324   0.03269   0.02696  -0.0599   0.1225   1.0000
   8.750   1.1399   0.03421   0.02848  -0.0591   0.1198   1.0000
   9.000   1.1478   0.03573   0.03000  -0.0584   0.1171   1.0000
   9.250   1.1554   0.03739   0.03167  -0.0578   0.1153   1.0000
   9.500   1.1652   0.03888   0.03316  -0.0573   0.1134   1.0000
   9.750   1.1744   0.04040   0.03466  -0.0567   0.1101   1.0000
  10.000   1.1868   0.04167   0.03594  -0.0562   0.1085   1.0000
  10.250   1.1995   0.04292   0.03720  -0.0558   0.1073   1.0000
  10.500   1.2108   0.04430   0.03859  -0.0553   0.1060   1.0000
  10.750   1.2206   0.04586   0.04016  -0.0548   0.1043   1.0000
  11.000   1.2316   0.04729   0.04159  -0.0544   0.1027   1.0000
  11.250   1.2422   0.04873   0.04303  -0.0539   0.1004   1.0000
  11.500   1.2535   0.05011   0.04440  -0.0534   0.0986   1.0000
  11.750   1.2660   0.05138   0.04568  -0.0530   0.0973   1.0000
  12.000   1.2791   0.05261   0.04693  -0.0526   0.0960   1.0000
  12.250   1.2907   0.05400   0.04834  -0.0522   0.0934   1.0000
  12.500   1.2977   0.05583   0.05014  -0.0518   0.0872   1.0000
  12.750   1.2998   0.05804   0.05222  -0.0511   0.0666   1.0000
  13.000   1.3042   0.06008   0.05419  -0.0505   0.0584   1.0000
  13.250   1.3138   0.06166   0.05576  -0.0501   0.0561   1.0000
  13.500   1.3226   0.06330   0.05741  -0.0497   0.0539   1.0000
  13.750   1.3299   0.06512   0.05923  -0.0492   0.0519   1.0000
  14.000   1.3396   0.06673   0.06088  -0.0489   0.0509   1.0000
  14.250   1.3489   0.06837   0.06253  -0.0485   0.0488   1.0000
  14.500   1.3581   0.07002   0.06419  -0.0482   0.0471   1.0000
  14.750   1.3675   0.07163   0.06581  -0.0478   0.0454   1.0000
  15.000   1.3773   0.07321   0.06740  -0.0475   0.0423   1.0000
  15.250   1.3833   0.07522   0.06941  -0.0472   0.0379   1.0000
  15.500   1.3889   0.07729   0.07145  -0.0469   0.0345   1.0000
  15.750   1.3959   0.07921   0.07336  -0.0467   0.0324   1.0000
  16.000   1.4033   0.08109   0.07525  -0.0465   0.0309   1.0000
  16.250   1.4114   0.08288   0.07706  -0.0462   0.0303   1.0000
  16.500   1.4171   0.08503   0.07925  -0.0461   0.0296   1.0000
  16.750   1.4233   0.08711   0.08135  -0.0460   0.0289   1.0000
  17.000   1.4298   0.08917   0.08343  -0.0459   0.0283   1.0000
  17.250   1.4361   0.09127   0.08556  -0.0459   0.0277   1.0000
  17.500   1.4400   0.09372   0.08804  -0.0460   0.0272   1.0000
  17.750   1.4462   0.09589   0.09026  -0.0461   0.0269   1.0000
  18.000   1.4529   0.09799   0.09240  -0.0462   0.0267   1.0000
  18.250   1.4592   0.10018   0.09463  -0.0464   0.0265   1.0000
  18.500   1.4631   0.10274   0.09724  -0.0467   0.0262   1.0000
  18.750   1.4684   0.10511   0.09966  -0.0470   0.0260   1.0000
  19.000   1.4739   0.10747   0.10206  -0.0474   0.0257   1.0000
  19.250   1.4788   0.10989   0.10452  -0.0478   0.0254   1.0000
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