Multinozzle Plume Flowfields.
Abstract
The a priori prediction of multinozzle rocket exhaust flow fields is addressed in detail. The requirements for accurate prediction of plume signature are derived and new quantitative relationships between optical signal and plume properties are derived. It is shown that, among a variety of requirements, plume models must include an accurate detailed description of the three dimensional near field of the multinozzle plume self impingement to achieve accuracy and reliability. The qualitative structure of these complex three dimensional flow fields is discussed. Several of the regulating flow process thus identified are three dimensional in nature and have no counterparts in classical two dimensional supersonic flow theory. One such process, the intersection of two three dimensional shock surfaces, is analyzed in detail and a qualitative account of the developing pattern is given. A three dimensional 'floating fitted shock' numerical technique was devised for the first time. The computer code employs discrete discontinuities including plume boundary, shock surface and a Complex singularity all which propagate through a fixed computational grid. The code was used successfully for the computation of the impingement of two uniform rectangular jets. A new analysis for the mach disc flow field in an axisymmetric plume was derived.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1981
- Accession Number
- ADA097244
Entities
People
- Stanley Rudman
Organizations
- Grumman