Date of Award
12-1994
Document Type
Thesis
Degree Name
Master of Science in Astronautical Engineering
Department
Department of Aeronautics and Astronautics
First Advisor
Rodney Bowersox, PhD
Abstract
This study used a range of low blowing ratios with air through an area of porous material in a Mach 2.0 nozzle to quantity the change in boundary layer thickness as a function of blowing ratio. Also, exit and wall Mach number profiles at each blowing ratio were collected to characterize performance losses as a result of blowing. Performance in terms of specific impulse was also studied. As expected, the boundary layer thickness increased and nozzle performance in terms of exit Mach number decreased with increasing blowing ratio.
AFIT Designator
AFIT-GA-ENY-94D-3
DTIC Accession Number
ADA289393
Recommended Citation
Keener, David N., "Investigation of Boundary Layer and Performance Effects of Transpiration Cooling through a Porous Plate in a Rocket Nozzle" (1994). Theses and Dissertations. 6329.
https://scholar.afit.edu/etd/6329