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

WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il)

WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL - NASA/Langley Whitcomb integral supercritical airfoil


Airfoil whitcomb-il
Details Dat file Parser  
(whitcomb-il) WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL
NASA/Langley Whitcomb integral supercritical airfoil
Max thickness 11% at 35% chord.
Max camber 2.4% at 82.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL
 37.        37.
 
 0.0      0.0
  .0075    .0176
  .0125    .0215
  .0250    .0276
  .0375    .0316
  .0500    .0347
  .0750    .0394
  .1000    .0428
  .1250    .0455
  .1500    .0476
  .1750    .0493
  .2000    .0507
  .2500    .0528
  .3000    .0540
  .3500    .0547
  .4000    .0550
  .4500    .0548
  .5000    .0543
  .5500    .0533
  .5750    .0527
  .6000    .0519
  .6250    .0511
  .6500    .0501
  .6750    .0489
  .7000    .0476
  .7250    .0460
  .7500    .0442
  .7750    .0422
  .8000    .0398
  .8250    .0370
  .8500    .0337
  .8750    .0300
  .9000    .0255
  .9250    .0204
  .9500    .0144
  .9750    .0074
 1.0000   -.0008
 
 0.0      0.0
  .0075   -.0176
  .0125   -.0216
  .0250   -.0281
  .0375   -.0324
  .0500   -.0358
  .0750   -.0408
  .1000   -.0444
  .1250   -.0472
  .1500   -.0493
  .1750   -.0510
  .2000   -.0522
  .2500   -.0540
  .3000   -.0548
  .3500   -.0549
  .4000   -.0541
  .4500   -.0524
  .5000   -.0497
  .5500   -.0455
  .5750   -.0426
  .6000   -.0389
  .6250   -.0342
  .6500   -.0282
  .6750   -.0215
  .7000   -.0149
  .7250   -.0090
  .7500   -.0036
  .7750    .0012
  .8000    .0053
  .8250    .0088
  .8500    .0114
  .8750    .0132
  .9000    .0138
  .9250    .0131
  .9500    .0106
  .9750    .0060
 1.0000   -.0013
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

DSMA-523B AIRFOILPreviewDetails
DSMA-523A AIRFOILPreviewDetails
NPL 9510 AIRFOILPreviewDetails
NASA SC(2)-0712 AIRFOILPreviewDetails
NASA SC(2)-0710 AIRFOILPreviewDetails
NYU/GRUMMAN K-1 AIRFOILPreviewDetails
NASA SC(2)-0612 AIRFOILPreviewDetails
NASA SC(2)-0610 AIRFOILPreviewDetails
BOEING AIRFOIL J (no closed TE)PreviewDetails
NASA SC(2)-0412 AIRFOILPreviewDetails

Polars for WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   whitcomb-il50,000922.1 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   whitcomb-il50,000519.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   whitcomb-il100,000922.9 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   whitcomb-il100,000527.8 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   whitcomb-il200,000930.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   whitcomb-il200,000539.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   whitcomb-il500,000949.1 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   whitcomb-il500,000559.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   whitcomb-il1,000,000969 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   whitcomb-il1,000,000576.9 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit