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DOUGLAS LA203A AIRFOIL (la203a-il)

DOUGLAS LA203A AIRFOIL - Douglas/Liebeck LA203A high lift airfoil


Airfoil la203a-il
Details Dat file Parser  
(la203a-il) DOUGLAS LA203A AIRFOIL
Douglas/Liebeck LA203A high lift airfoil
Max thickness 15.7% at 34.3% chord.
Max camber 5.5% at 46% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
DOUGLAS LA203A AIRFOIL
   51.       51.

  0.000000  0.000000
  0.000887  0.006000
  0.003544  0.015836
  0.007963  0.023336
  0.014127  0.030677
  0.022015  0.038031
  0.031599  0.045492
  0.042846  0.053047
  0.055715  0.060636
  0.070162  0.068190
  0.086135  0.075641
  0.103579  0.082919
  0.122432  0.089956
  0.142628  0.096688
  0.164095  0.103048
  0.186758  0.108970
  0.210538  0.114389
  0.235350  0.119234
  0.261106  0.123424
  0.287718  0.126854
  0.315090  0.129435
  0.343127  0.131182
  0.371729  0.132075
  0.400796  0.132090
  0.430226  0.131219
  0.459916  0.129436
  0.489759  0.126743
  0.519653  0.123176
  0.549490  0.118770
  0.579167  0.113566
  0.608579  0.107640
  0.637621  0.101087
  0.666193  0.094063
  0.694194  0.086797
  0.721524  0.079995
  0.748087  0.072292
  0.773791  0.065291
  0.798545  0.058545
  0.822261  0.052086
  0.844856  0.045936
  0.866250  0.040113
  0.886369  0.034630
  0.905141  0.029490
  0.922500  0.024700
  0.938385  0.020258
  0.952740  0.016162
  0.965516  0.012408
  0.976665  0.008985
  0.986151  0.005883
  0.993938  0.003044
  1.000000  0.000000

  0.000000  0.000000
  0.000887  -.008018
  0.003544  -.015137
  0.007963  -.021544
  0.014127  -.026516
  0.022015  -.029638
  0.031599  -.031320
  0.042846  -.032209
  0.055715  -.032676
  0.070162  -.032867
  0.086135  -.032657
  0.103579  -.032692
  0.122432  -.032407
  0.142628  -.032024
  0.164095  -.031557
  0.186758  -.031016
  0.210538  -.030405
  0.235350  -.029724
  0.261106  -.028967
  0.287718  -.028125
  0.315090  -.027184
  0.343127  -.026124
  0.371729  -.024919
  0.400796  -.023512
  0.430226  -.021826
  0.459916  -.019830
  0.489759  -.017533
  0.519653  -.014947
  0.549490  -.012099
  0.579167  -.009052
  0.608579  -.005917
  0.637621  -.002822
  0.666193  0.000143
  0.694194  0.002917
  0.721524  0.005448
  0.748087  0.007686
  0.773791  0.009596
  0.798545  0.011145
  0.822261  0.012313
  0.844856  0.013087
  0.866250  0.013484
  0.886369  0.013448
  0.905141  0.013056
  0.922500  0.012302
  0.938385  0.011218
  0.952740  0.009838
  0.965516  0.008211
  0.976665  0.006392
  0.986151  0.004425
  0.993938  0.002384
  1.000000  0.000000
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Lednicer format dat file
Selig format dat file

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Polars for DOUGLAS LA203A AIRFOIL (la203a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   la203a-il50,00096 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   la203a-il50,000513.7 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   la203a-il100,000930.6 at α=12.25°Mach=0 Ncrit=9Xfoil predictionDetails
   la203a-il100,000546.5 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   la203a-il200,000982.4 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   la203a-il200,000585.4 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   la203a-il500,0009127.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   la203a-il500,0005124 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   la203a-il1,000,0009160.5 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   la203a-il1,000,0005151.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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