THE INFLUENCE OF COMBUSTION OSCILLATIONS ON THE JET IN STILL AIR AND IN SUPERSONIC FLIGHT,
Abstract
The equations of unsteady motion for compressible flow were linearized under the assumption of small perturbations in the uniform parallel jet and exterior streams. The equations were solved for a supersonic jet issuing into still air and for a supersonic jet into a supersonic stream by means of the Laplace transformation in the time and axial variables. The boundary conditions of continuous pressure and flow inclination along the jet and stream interface were satisfied on the undisturbed location of the interface and the perturbation pressure at the jet exit was assumed to be cosinusoidal. The shape of the jet boundary and density perturbation in the jet stream were computed for several two dimensional flows. Near the jet exit the jet boundary deflection has maximum and minimum amplitudes at the points where the two interior Mach lines from the edges of the jet exit and their reflections intersect the jet interface. The transform solutions for axially symmetric flow were also obtained, but only the shape of the jet boundary in still air was computed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1967
- Accession Number
- AD0660055
Entities
People
- F. Edward Ehlers
Organizations
- Boeing