Multi Electrode Shock Attenuation Model Design

Completed TRL 3 (started at 2, targeting 3)

Description

This study is in support of ongoing research in the area of plasma based energy deposition and shock wave attenuation i.e. sonic boom. Currently general design of quieter supersonic aircraft leverages passive techniques for sonic boom mitigation including shaping; long nose and highly swept wings for example. And strategic placement of the engine inlet in order to minimize the sonic boom heard on the ground. Although this type of design philosophy shows positive results with regards to sonic boom mitigation, it places restrictions on the shape and carrying capacity of the aircraft. Also, aircraft based on this design philosophy have poor handling qualities, especially at low speeds. The application of plasma dynamics to sonic boom reduction has the potential to loosen some of the design restrictions encountered with shape optimization. This research introduces the possibility of having wider and larger commercial supersonic airplanes with a larger carrying capacity and improved handling qualities.

Benefits

Electric discharge at the nose of a cone cylinder model in Mach 2 supersonic flow has been shown to significantly affect the shockwaves generated by the model. This holds significant promise as a method of sonic boom mitigation. The main requirement for the observed effects on the shockwaves is that the discharge have an axisymmetric distribution about the nose of the model. The original model had one annular electrode which did not consistently generate an axisymmetric discharge. For this project we would like to design, build and test a cone cylinder model with multiple electrodes at the tip in order to generate an approximately asymmetric arc distribution at that location. We will be considering different discharge patterns to determine the most optimal design. A well controlled electric arc would tie into ongoing research into the far field impact of plasma based energy deposition on shock wave attenuation. Success in this research would usher the way for a game changing tool to use in the design of quieter supersonic aircraft.

Details

Technology area	Sensors and Instruments
Program	Center Innovation Fund: AFRC CIF (AFRC CIF)
Lead organization	Armstrong Flight Research Center, Edwards, CA
Start date	2020-10-01
End date	2021-09-30

Project contacts

Listed on TechPort itself — the most direct way to ask about this specific project.

Aliyah N Ali — aliyah.n.ali@nasa.gov

How to get involved

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