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

NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il)

NASA/LANGLEY LS(1)-0421MOD AIRFOIL - NASA/Langley LS(1)-0421MOD general aviation airfoil


Airfoil ls421mod-il
Details Dat file Parser  
(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD AIRFOIL
NASA/Langley LS(1)-0421MOD general aviation airfoil
Max thickness 21% at 32.5% chord.
Max camber 2.3% at 30% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 NASA/LANGLEY LS(1)-0421MOD AIRFOIL
45.        45.
 
 0.00000   0.00000
  .00200    .01560
  .00500    .02430
  .01250    .03830
  .02500    .05400
  .03750    .06510
  .05000    .07360
  .07500    .08650
  .10000    .09600
  .12500    .10340
  .15000    .10930
  .17500    .11410
  .20000    .11790
  .22500    .12080
  .25000    .12290
  .27500    .12430
  .30000    .12500
  .32500    .12500
  .35000    .12440
  .37500    .12330
  .40000    .12170
  .42500    .11960
  .45000    .11700
  .47500    .11400
  .50000    .11060
  .52500    .10680
  .55000    .10270
  .57500    .09830
  .60000    .09360
  .62500    .08860
  .65000    .08330
  .67500    .07780
  .70000    .07210
  .72500    .06620
  .75000    .06010
  .77500    .05390
  .80000    .04760
  .82500    .04120
  .85000    .03480
  .87500    .02840
  .90000    .02200
  .92500    .01560
  .95000    .00910
  .97500    .00250
 1.00000   -.00420
 
 0.00000   0.00000
  .00200   -.01070
  .00500   -.01770
  .01250   -.02650
  .02500   -.03520
  .03750   -.04160
  .05000   -.04680
  .07500   -.05500
  .10000   -.06140
  .12500   -.06650
  .15000   -.07070
  .17500   -.07410
  .20000   -.07700
  .22500   -.07940
  .25000   -.08130
  .27500   -.08280
  .30000   -.08390
  .32500   -.08460
  .35000   -.08490
  .37500   -.08490
  .40000   -.08460
  .42500   -.08390
  .45000   -.08280
  .47500   -.08130
  .50000   -.07940
  .52500   -.07700
  .55000   -.07400
  .57500   -.07050
  .60000   -.06660
  .62500   -.06230
  .65000   -.05760
  .67500   -.05250
  .70000   -.04720
  .72500   -.04180
  .75000   -.03640
  .77500   -.03100
  .80000   -.02560
  .82500   -.02060
  .85000   -.01590
  .87500   -.01180
  .90000   -.00860
  .92500   -.00700
  .95000   -.00690
  .97500   -.00880
 1.00000   -.01320
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA 2421PreviewDetails
B-29 ROOT AIRFOILPreviewDetails
AH 93-W-215PreviewDetails
GOE 683 AIRFOILPreviewDetails
EPPLER 1214 AIRFOILPreviewDetails
GOE 703 AIRFOILPreviewDetails
GOE 770 AIRFOILPreviewDetails
FX 84-W-218PreviewDetails
NACA 65(4)-421 a=0.5PreviewDetails
NACA 4421PreviewDetails

Polars for NASA/LANGLEY LS(1)-0421MOD AIRFOIL (ls421mod-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ls421mod-il50,00097.2 at α=0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ls421mod-il50,000518.6 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ls421mod-il100,000937.2 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ls421mod-il100,000538.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   ls421mod-il200,000951.9 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   ls421mod-il200,000556 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   ls421mod-il500,000980.8 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   ls421mod-il500,000577.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   ls421mod-il1,000,0009100 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ls421mod-il1,000,000590.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit