Propulsion Nozzle Studies. Volume II. Design of Maximum Thrust Nozzle-Base-Boattail Contours.
Abstract
A production-type computer program was developed for the design of maximum thrust axisymmetric nozzle-base-boattail contours. The flow field analysis is based on the governing equations for the rotational flow of a frozen or equilibrium gas mixture. The contour optimization is based on the direct optimization of a nonlinear function of several (three or less) geometric variables. The nozzle and boattail contours are modeled as a second-order polynomial and a cone, respectively. For fixed initial contours and nozzle and boattail lengths, the second-order polynomial nozzle contour is uniquely specified by the nozzle throat attachment angle and the nozzle exit lip radius, and the conical boattail is uniquely specified by the boattail exit lip radius. These three independent parameters are varied to determine the unique nozzle-base-boattail configuration that yields maximum thrust. Three methods are included in the program to determine the maximum thrust contour. Each method requires an initial estimate of the geometry that produces maximum thrust. The three methods were also applied to the design of nozzle-base-boattail configurations. The three-dimensional optimizations were found to be practical for finding the maximum thrust attainable for a nozzle-base-boattail assembly. Each of the three methods converged efficiently to the maximum thrust nozzle-base-boattail contour.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1977
- Accession Number
- ADA041530
Entities
People
- Jeffrey G. Allman
- Joe D. Hoffman
Organizations
- Purdue University