The Transonic Flow Field for a Fluidic-Generator Fuze Assembly.
Abstract
An experimental program has been conducted to evaluate the performance of the fluidic-generator fuze assembly of the Army's Multi-Launch Rocket System (MLRS) in the transonic speed range. Static-pressure measurements and Pitot-pressure measurements were obtained for different nose configurations during a test program which was conducted in the Aerodynamic Wind Tunnel at the Arnold Engineering Development Center. The test conditions included free-stream Mach numbers from 0.95 to 1.3 over a range of free-stream densities simulating altitudes from 15,240 m to 21,030 m. The pressure data from these tests have been analyzed to describe the internal and the external flow fields. The pressures measured at the inlet hole for the fluidic-generator assembly is in close agreement with that given by the normal shock relations. The experimentally determined pressure ratio (p/p sub t2) decreased as the free-stream Mach number increased for all external orifices from x = 0.030 x sub 0 to 1.000 x sub 0. These Mach-number variations were gradual and consistent. Since flow through the fluidic-generator assembly is choked by the nozzle centerbody, the mass-flow rate can be correlated in terms of the external flow conditions.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1981
- Accession Number
- ADA099616
Entities
People
- John J. Bertin
- Richard L. Goodyear
- Timothy E. Hayden
Organizations
- University of Texas at Austin