Accession Number:

AD0620246

Title:

A COMPARISON OF THE THEORETICAL DETERMINATION OF THE DEVELOPMENT OF THE BOUNDARY LAYER MOMENTUM THICKNESS IN AN ARBITRARY PRESSURE GRADIENT WITH FULL- SCALE FLIGHT EXPERIMENTS ON A POROUS AIRFOIL SECTION WITH TRANSPIRATION

Descriptive Note:

Research rept.

Corporate Author:

MISSISSIPPI STATE UNIV MISSISSIPPI STATE DEPT OF AEROPHYSICS

Personal Author(s):

Report Date:

1965-07-01

Pagination or Media Count:

38.0

Abstract:

Calculation of the turbulent boundary layer momentum thickness around a NACA 4416 airfoil section was made by a successive approximation method developed for two-dimensional and axisymmetric flows. These results are compared with experimental results obtained from flight tests with a sailplane--Schweizer TG-3--with reasonable results.

Subject Categories:

  • Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE