MHD Flow Control
Abstract
This report results from a contract tasking Institute of High Temperatures RAS as follows: Task I: Renewed scientific interest has arisen throughout the world as to the potential application of Magneto Hydrodynamics (MHD) processes for advancement of flight. Among the areas of interest is the utilization of MHD as a means for enhancing the speed and range of scramjets through a concept known as MHD energy bypass. Currently. scramjet operation is limited to free stream flight Mach numbers around 10. This limitation arises from the excessive temperature that develops at high Mach conditions as a result of the slowing down of the propulsion drafted hypersonic air stream within the propulsion system inlet. The extra benefit of this proposed Project is the experimental facility to be used for experimental studies of MHO effects in hypervelocity flows that is an MHD assisted wind tunnel. Therefore, operation of this facility will provide valuable information on MHD interaction taking place in MHD accelerator. All experimental results can be and will be used to validate existing computer codes for such processes. Task 2: One of the main problems of stable combustion in high-speed flow is an effective mixing of gaseous fuel and oxidant providing full combustion during the resident time in combustor chamber. Generally speaking in-flow mixing consists of two main mechanisms: kinematics mixing (convection) and molecular diffusion. The latter is a final stage of mixing needed to provide extended combustible mixture. Kinematics mixing is more effective in vortex flows; the higher vortices the better kinematics mixing which means the larger fuel/oxidant interface surface. The second mixing mechanisms, diffusion, forms a reacting volume estimated as the interface surface times diffusion length.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 2006
- Accession Number
- ADA473536
Entities
People
- Valentin A. Bityurin
Organizations
- Russian Academy of Sciences