RECOVERY FACTORS FOR AND HEAT-TRANSFER COEFFICIENTS TO AIR FLOWING IN A TUBE AT SUPERSONIC VELOCITY
Abstract
An experimental and analytical study was conducted on the flow of air in the entrance region of a tube for inlet Mach numbers of about 3.0 and 5.0. It was found that a laminar boundary layer exists on the walls of the tu e for some distance downstream of the tube inlet with an isentropic core of fluid located outside the boundary layer region and around the tube centerline. The laminar boundary layer develops along the tube until length Reynolds numbers are reached which permit transition to a t rbulent boundar layer. The isentropic core of fluid xists after transition has taken place and until the turbulent boundary layer fills the entire cross sectional area of the tube. As the inlet diameter Reynolds number was increased, the distance between the tube inlet and the point of transition decreased. This flow model was verified for inlet Mach numbers up to about 5.0 and for inlet diameter Reynolds numbers up to about 10 to the 6th power. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1961
- Accession Number
- AD0265878
Entities
People
- George A. Brown
Organizations
- Massachusetts Institute of Technology