Accession Number : ADA268106


Title :   An Investigation of Oblique Shock/Boundary Layer Interaction Control


Descriptive Note : Final rept. 1 Dec 90-31 Mar 93,


Corporate Author : CINCINNATI UNIV OH DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS


Personal Author(s) : Hamed, A


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a268106.pdf


Report Date : 30 Jun 1993


Pagination or Media Count : 15


Abstract : The objective of this work is to provide a basic understanding of the flow in the shock boundary layer interactions and of the mechanisms of their control. A parametric investigation was conducted to determine the effect of bleed configuration on the flow in the interaction region of an incident oblique shock with a turbulent boundary layer. Results of the numerical flow simulations were obtained for different slot widths, depths and slat angles over a bleed mass flow range between zero and choked conditions. The bleed results reveal a complex structure of compression expansion wave system over the bleed port entrance, and different levels of flow operation inside the slot. Code development for the implicit numerical solution of the two dimensional compressible Navier-Stokes and K- Epsilon equations was completed. The code was used in the simulation of unsteady supersonic cavity flow and the results compared with experimental data.... Shock boundary layer bleed interactions.


Descriptors :   *AEROSPACE CRAFT , *SUPERSONIC FLOW , *BOUNDARY LAYER FLOW , MATHEMATICAL MODELS , SIMULATION , ANGLES , INTERACTIONS , SHOCK WAVES , NAVIER STOKES EQUATIONS , BOUNDARY LAYER , TURBULENT BOUNDARY LAYER , CAVITIES , MASS FLOW , CONFIGURATIONS , SHOCK


Subject Categories : Aerodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE