Accession Number : AD0618323

Title :   FULLY DEVELOPED TURBULENT SUPERSONIC FLOW IN RECTANGULAR CHANNELS.

Descriptive Note : Flight sciences laboratory rept.,

Corporate Author : BOEING SCIENTIFIC RESEARCH LABS SEATTLE WASH

Personal Author(s) : Richmond,J. Kenneth ; Goldstein,Raymond

Report Date : MAY 1965

Pagination or Media Count : 1

Abstract : In order to assess properly the gas dynamic aspects of MHD channel flow it is necessary to obtain details of the flow conditions before fields are applied. In a channel with an entrance cross section of one cm square, with lengths up to 20 cm, at a Mach number of about 1.5 and at static pressures approaching one atm, a turbulent boundary layer fills the channel, and fully developed pipe flow turbulence prevails. A simple one-dimensional theory is presented for this case, relating stagnation pressure change to area change, heat transfer and friction factor. Experiments are described in which a supersonic flow of heated or cold argon was passed into the channel, and the flow rate and temperature varied to cover a range of Reynolds numbers (based on channel width) from 5,000 to 500,000. Total pressure and total temperature changes are correlated with the theory to indicate the progress of boundary layer development and the parameters affecting the friction and heat transfer coefficients. (Author)

Descriptors :   (*RECTANGULAR BODIES, SUPERSONIC CHARACTERISTICS), (*SUPERSONIC FLOW, TURBULENCE), (*MAGNETOHYDRODYNAMICS, SUPERSONIC FLOW), FRICTION, PARTICLE ACCELERATORS, TURBULENT BOUNDARY LAYER, HEAT TRANSFER, ARGON, STAGNATION POINT, PRESSURE, REYNOLDS NUMBER, ONE DIMENSIONAL FLOW

Distribution Statement : APPROVED FOR PUBLIC RELEASE