Design of an Optimum Thrust Nozzle for a Typical Hypersonic Trajectory Through Computational Analysis

Author

David J. Herring

Date of Award

12-1991

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

John H. Doty, PhD

Abstract

An analysis of a planar supersonic nozzle for a NASP type vehicle was performed with a computer program that used the new upwind flux difference splitting (FDS) method. Thrust optimization, off-design performance, and cowl angle parametric analyses were accomplished, using FDS code, an oblique shock wave solver program, and a Scramjet cycle analysis code, at six points on a 1000 PSF maximum dynamic pressure trajectory, for the Mach numbers 7.5, 10.0, 12.5, 15.0, 17.5, and 20.0. Results from the single parameter number range from 7.5 to 20.0, the attachment angles identified as optimum for the respective trajectory points were 38.0, 38.6, 30.0, 24.6, 20.6, and 17.8. From this range of angles, the 20.6 degree nozzle was found to produce the minimum off-design performance losses over the entire trajectory. this deteriorization was based on selection criteria biased toward the higher Mach numbers. Using the 20.6 degree nozzle attachment angle, a cowl angle parametric analysis was performed to determine the extent to which off design performance losses could be recovered.

AFIT Designator

AFIT-GAE-ENY-91D-11

DTIC Accession Number

ADA243870

Comments

The author's Vita page is omitted.

Recommended Citation

Herring, David J., "Design of an Optimum Thrust Nozzle for a Typical Hypersonic Trajectory Through Computational Analysis" (1991). Theses and Dissertations. 7462.
https://scholar.afit.edu/etd/7462