Date of Award
6-1993
Document Type
Thesis
Degree Name
Master of Science
Department
Department of Aeronautics and Astronautics
First Advisor
John H. Doty, PhD
Abstract
This computational study of a hypersonic sub-scale nozzle/cowl configuration compares numerical solutions with experimental data for nozzle performance at off design conditions (subsonic through supersonic Mach numbers. A combination of Van Leer and Roe flux-splitting algorithms was used to solve the flow field. The explicit formulation assumed laminar planar flow and the perfect gas equation of state. A validation for the numerical algorithm was accomplished by comparing with experimental data for a variety of cases. Grid refinement, geometry, and operating conditions all influenced the comparison of the experimental and computational data. Generally, as the Mach number and nozzle pressure ratio increased, the consistency between the experimental results showed better agreement, although the computational investigation was performed on the basis of planar, laminar flow. For the different cowl configurations, the results for baseline and -5 degree cowl show a better agreement than the long and +5 degree cowl.
AFIT Designator
AFIT-GAE-ENY-93J-02
DTIC Accession Number
ADA266543
Recommended Citation
Hyun, Yonghee, "A Comparison of Computational and Experimental Data for a Subscale High Speed Propulsive Nozzle at Low Mach Numbers" (1993). Theses and Dissertations. 7063.
https://scholar.afit.edu/etd/7063
Comments
The author's Vita page is omitted.