Accession Number : ADA289793

Title :   The Effect of Viscous Attenuation on Shock Tube Performance.

Descriptive Note : Master's thesis,

Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Personal Author(s) : McKenzie, Nick R.

PDF Url : ADA289793

Report Date : DEC 1994

Pagination or Media Count : 76

Abstract : Shock wave attenuation affects experimental results by reducing results shock velocity as it travels down the shock tube. Until recently, attenuation has not been readily predictable with accuracy and was simply accepted during the experimental process. A mass loss theory was developed by Dr. Harold Mirels which accounted for the shock wave attenuation by considering the formed boundary layer due to the passage of a shock wave. The purpose of this thesis to develop a computer code, which would apply Mirels' theory to a prediction model, and validate the results with acoustic theory and Mirels' data. It will then be used to determine an accurate shock velocity for an additional shock tube. The computer results will be proven to match the experimental data well. However, additional corrections involying friction, heating, and real gas effects are needed to produce excellent results. It will also be discovered that mass loss correction results are a significant part of the total shock wave attenuation. (MM)

Descriptors :   *COMPUTER PROGRAMS, *SHOCK WAVES, *VISCOUS FLOW, *SHOCK TUBES, VELOCITY, ACOUSTIC WAVES, THESES, TURBULENT BOUNDARY LAYER, GAS DYNAMICS, FORTRAN, MASS FLOW, WAVE PROPAGATION, AEROSPACE ENVIRONMENTS, ATTENUATION, MACH NUMBER, FRICTION, ENTHALPY, SOUND PRESSURE, SPECIFIC HEAT, EQUATIONS OF STATE, BOUNDARY LAYER FLOW.

Subject Categories : Computer Programming and Software
      Test Facilities, Equipment and Methods

Distribution Statement : APPROVED FOR PUBLIC RELEASE