Experimental Investigation of a Supersonic Turbulent Boundary Layer with Adverse Pressure Gradient

Author

Chad S. Hale

Date of Award

12-1995

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Rodney Bowersox, PhD

Abstract

Laser Doppler Velocimetry (LDV) measurements were made to quantify the effect of adverse pressure gradient on the compressible turbulent flow structure in a Mach 2.9 boundary layer (Re/m= 1.75 x 10⁷). Measurements included profiles of 2-D mean velocities, turbulence intensities, Reynolds shear stresses, intermittency, flatness and skewness. In addition, mean strain rates were also measured. The boundary layer measurements were acquired for both flat plate and compression ramp models. LDV measurements were made at two locations on the compression ramp model at 68 cm and 71 cm downstream of the nozzle throat. At these locations, Β ≈ 1.12 and -0.94, respectively. Flow visualization was accomplished by nanosecond shadowgraph and schlieren photography. Results indicate that the adverse pressure gradient increased the Reynolds shear stresses by 190% and turbulence intensities by 24% of the flat plat values. In the favorable pressure gradient region, these quantities were decreased by 52% and 7% with respect to the adverse pressure gradient values, respectively.

AFIT Designator

AFIT-GAE-ENY-95D-12

DTIC Accession Number

ADA309625

Recommended Citation

Hale, Chad S., "Experimental Investigation of a Supersonic Turbulent Boundary Layer with Adverse Pressure Gradient" (1995). Theses and Dissertations. 6097.
https://scholar.afit.edu/etd/6097