Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

LA2573A (la2573a-il)

LA2573A - Liebeck LA2573A airfoil


Airfoil la2573a-il
Details Dat file Parser  
(la2573a-il) LA2573A
Liebeck LA2573A airfoil
Max thickness 13.7% at 28.8% chord.
Max camber 3.2% at 26.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
LA2573A
1.000000        0.000000
0.993938        0.000208
0.986151        0.000395
0.976665        0.000666
0.965516        0.001087
0.952740        0.001687
0.938385        0.002493
0.922500        0.003534
0.905141        0.004833
0.886369        0.006416
0.866250        0.008302
0.844856        0.010505
0.822261        0.013042
0.798545        0.015921
0.773791        0.019148
0.748087        0.022729
0.721524        0.026661
0.694194        0.030937
0.666193        0.035547
0.637621        0.040473
0.608579        0.045695
0.579167        0.051179
0.549490        0.056883
0.519653        0.062769
0.489759        0.068788
0.459916        0.074879
0.430226        0.080959
0.400796        0.086839
0.371729        0.092096
0.343127        0.096270
0.315090        0.099024
0.287718        0.100366
0.261106        0.100426
0.235350        0.099312
0.210538        0.097141
0.186758        0.094037
0.164095        0.090120
0.142628        0.085490
0.122432        0.080252
0.103579        0.074508
0.086135        0.068347
0.070162        0.061892
0.055715        0.055261
0.042846        0.048530
0.031599        0.041777
0.022015        0.035071
0.014127        0.028440
0.007963        0.021674
0.003544        0.014625
0.000887        0.007506
0.000000        0.000000
0.000887        -0.007494
0.003544        -0.014288
0.007963        -0.020299
0.014127        -0.024953
0.022015        -0.028018
0.031599        -0.029945
0.042846        -0.031348
0.055715        -0.032436
0.070162        -0.033303
0.086135        -0.034006
0.103579        -0.034581
0.122432        -0.035054
0.142628        -0.035447
0.164095        -0.035772
0.186758        -0.036040
0.210538        -0.036257
0.235350        -0.036426
0.261106        -0.036549
0.287718        -0.036625
0.315090        -0.036652
0.343127        -0.036627
0.371729        -0.036543
0.400796        -0.036397
0.430226        -0.036181
0.459916        -0.035890
0.489759        -0.035513
0.519653        -0.035045
0.549490        -0.034478
0.579167        -0.033803
0.608579        -0.033012
0.637621        -0.032097
0.666193        -0.031049
0.694194        -0.029854
0.721524        -0.028503
0.748087        -0.026973
0.773791        -0.025237
0.798545        -0.023222
0.822261        -0.020738
0.844856        -0.018088
0.866250        -0.015442
0.886369        -0.012892
0.905141        -0.010507
0.922500        -0.008334
0.938385        -0.006405
0.952740        -0.004735
0.965516        -0.003332
0.976665        -0.002191
0.986151        -0.001300
0.993938        -0.000604
1.000000        0.000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EPPLER 329 AIRFOILPreviewDetails
MARSKE XM-1D AIRFOIL (F14-3.0)PreviewDetails
EPPLER 341 AIRFOILPreviewDetails
EPPLER 328 AIRFOILPreviewDetails
EPPLER 338 AIRFOILPreviewDetails
Eiffel 371 (Monge)PreviewDetails
EPPLER 337 AIRFOILPreviewDetails
EPPLER 625 AIRFOILPreviewDetails
EPPLER 340 AIRFOILPreviewDetails
EPPLER 342 AIRFOILPreviewDetails

Polars for LA2573A (la2573a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   la2573a-il50,00096.9 at α=-0.5°Mach=0 Ncrit=9Xfoil predictionDetails
   la2573a-il50,000513.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   la2573a-il100,000915.7 at α=14.25°Mach=0 Ncrit=9Xfoil predictionDetails
   la2573a-il100,000527.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   la2573a-il200,000962.3 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   la2573a-il200,000564.9 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   la2573a-il500,0009102.6 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   la2573a-il500,000595.3 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   la2573a-il1,000,0009125.8 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   la2573a-il1,000,0005110.9 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit