Accession Number : ADA336192

Title :   Experimental Investigation of Combustion Stabilization in Supersonic Flow Using Free Recirculation Zones

Descriptive Note : Final rept.

Corporate Author : CENTRAL AERODYNAMIC INST MOSCOW (RUSSIA)

PDF Url : ADA336192

Report Date : AUG 1997

Pagination or Media Count : 57

Abstract : Final report summarizes shortly main results of the quarterly reports and presents experimental results on self-ignition and combustion stabilization in supersonic flow using free recirculation zone. Tests are conducted at hypersonic facility TsAGI T-131B. Measurements are performed in a nearly matched supersonic jet at the exit of two-dimensional channel over Mach number range M=2.O-2.8 at stagnation temperature range Tt=1200-1400K. initial thickness of jet was equal 67 mm. Self-ignition and stabilization are obtained at Tt=1400K. Self-ignition was absent at Tt=1200K, 1300K. Thickness of free recirculation zone was about 25-30 mm.

Descriptors :   *COMBUSTION STABILITY, *SUPERSONIC FLOW, *AUTOIGNITION, RUSSIA, MACH NUMBER, SUPERSONIC COMBUSTION, RECIRCULATION.

Subject Categories : Fluid Mechanics
      Combustion and Ignition

Distribution Statement : APPROVED FOR PUBLIC RELEASE