CFD Methods for High Speed Flows

Mach 6 Nozzle Design & Fabrication

Mach 6 Nozzle

The development of new Army projectiles requires aerodynamic testing in Mach Number 5 to 6. One of the major objectives of the present work is to extend the capabilities of the existing Shock Tube Research Facility to accommodate testing in the Mach Number range of 5 to 6. This has been accomplished by integrating a new Mach 6 nozzle into the existing shock tube. A considerable effort of the present work has been developed into the design of the Mach 6 nozzle by carrying out Advanced Computational Fluid Dynamics (CFD) calculations. These numerical simulations provided detailed information of the flow field inside the nozzle. Since current state-of-the-art capabilities of CFD are limited due to inadequate computational speeds a two prongs approach was adopted to design the nozzle:

  1. A time-averaged, viscous 2-Dimensional CFD scheme has been used to calculate aero-thermodynamical quantities and flow patterns inside the nozzle including wall boundary layer effects.
  2. A time-dependent inviscid, quasi-one-dimensional flow TVD (Total Viariation Diminishing) Scheme was used to investigate the wave patterns inside the shock tube and the duration of the useful flow in the working section.

Grid Used in Adopted Design

Grid Used in Adopted Design

Mach Number Contour

Mach Number Contour