TANGO: A Nozzle Optimization Approach for High-Speed Test Facilities

Numerous facilities at the Arnold Engineering Development Complex (AEDC) provide hypersonic test conditions. Supersonic nozzles are used to generate the required Mach numbers to the test cell. Nozzle contours were generated in the 1950’s for using the Method of Characteristics (MoC) approach. Based on customer requirements, this project focused on improving the nozzle contours to provide more uniform Mach number and flow angularity at the nozzle exit which interfaces with the test section. The Tool for Automated Nozzle Generation and Optimization (TANGO) was created to optimize the flow quality at the nozzle exit using Computational Fluid Dynamics (CFD) and finite element Computational Structural Dynamics (CSD) methods.

TANGO has been applied to contours to meet the criteria established for flow quality, as well as structural integrity. The optimization criteria are based on the target Mach number, pressure uniformity, and flow angularity. TANGO has also been applied to other flexible wall nozzles and has been extended to axisymmetric nozzles, where Bezier curve control points are utilized for optimization. More details will be given in the final presentation.

PRESENTER

Jenkins, Cooper
cooper.jenkins.ctr@us.af.mil
931-454-6434

National Aerospace Solutions

CO-AUTHORS

Robinson, Christopher
christopher.robinson.32@us.af.mil

Power, Greg
gregory.power.1@us.af.mil

CATEGORY

Computational Fluid Dynamics

SYSTEMS USED

Narwhal, Warhawk

SECRET

No