Accession Number : AD0481503
Title : FLOW NONUNIFORMITY IN SHOCK TUBES OPERATING AT MAXIMUM TEST TIME.
Descriptive Note : Technical documentary rept.,
Corporate Author : AEROSPACE CORP EL SEGUNDO CA LAB OPERATIONS
Personal Author(s) : Mirels, H.
Report Date : JAN 1966
Pagination or Media Count : 31
Abstract : Shock tube flow nonuniformity is investigated in the limit where the shock and contact surface have reached their maximum separation. Ideal gases are considered. It is found that all fluid properties increase in value between the shock and contact surface. The nonuniformity is greatest when gamma (ratio of specific heats) is large and M sub s (shock Mach number) is low. For gamma = 5/3 and M sub s > or = 3, the static temperature, density, and pressure increase by about 8, 12 and 20%, respectively; the stagnation temperature increases by about 35%, and the stagnation pressure, dynamic pressure, and stagnation point heat transfer increase by about a factor of 2. These results apply to turbulent as well as laminar boundary layers. The variation of flow properties with distance behind the shock, as well as particle time of flight, is given for both wholly laminar and wholly turbulent wall boundary layers. These results are particularly important for chemical rate and heat transfer studies. (Author)
Descriptors : (*SHOCK TUBES, FLUID DYNAMICS), SEPARATION, SPECIFIC HEAT, SUPERSONIC FLOW, SUPERSONIC CHARACTERISTICS, STAGNATION POINT, TEMPERATURE, PRESSURE, DENSITY, HEAT TRANSFER, TURBULENT BOUNDARY LAYER, LAMINAR BOUNDARY LAYER, ABLATION, HEAT SHIELDS, REENTRY VEHICLES, GAS DISCHARGES, THERMAL INSULATION, SHOCK WAVES, ATTENUATION, MATHEMATICAL ANALYSIS, EQUATIONS.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE