Comparison of an Axisymmetric and a Planar Shock Tunnel Nozzle

Abstract

In order to expand the capabilities of Texas A&M University’s Hypervelocity Expansion Tunnel to include a reflected shock tunnel mode of operation, a comparison study between axisymmetric and planar nozzles at varying Mach numbers was conducted. The nozzle curves were developed using method of characteristics codes that include viscous effects. Computational fluid dynamics simulations were conducted using ANSYS Fluent to validate these curves. Preliminary mechanical designs for both a variable Mach number planar nozzle and a Mach 8 axisymmetric nozzle were created using the computer aided design software Solidworks. From these results and gathered knowledge, comparisons between the two types of nozzles were performed, leading to a recommendation of which type would be best suited for both external aerodynamics and internal propulsion studies.