ScholarLens Back to search
1957•Unpublished venueRequires access

Combustor performance of a 16-inch ram jet using gaseous hydrogen as fuel at Mach number 3.0

J. F. Wasserbauer, Fred A Wilcox

Open publisher page 2 citations

Abstract

An investigation was conducted in the NACA Lewis 10- by 10-foot supersonic wind tunnel to evaluate the performance of three burner configurations in a 16-inch ram jet with gaseous hydrogen as fuel. Data were obtained over a fuel-air-ratio range from 0.0030 to 0.0260 (stoichiometric = 0.0292) at a free-stream Mach number of 3.0 and 0 degree angle of attack. The exit nozzle-throat area ratios employed were 0.60 and 0.75.

About this research paper

What this paper is about

An investigation was conducted in the NACA Lewis 10- by 10-foot supersonic wind tunnel to evaluate the performance of three burner configurations in a 16-inch ram jet with gaseous hydrogen as fuel. Data were obtained over a fuel-air-ratio range from 0.0030 to 0.0260 (stoichiometric = 0.0292) at a free-stream Mach number of 3.0 and 0 degree angle of attack. The exit nozzle-throat area ratios employed were 0.60 and 0.75.

Why it matters

OpenAlex reports 2 citations for this work. Citation counts describe recorded attention and do not establish research quality.

Key contribution

A contribution statement is not available in the OpenAlex record.

Method / approach

Method details are not available in the OpenAlex metadata.

Main findings

Findings are not separately available in the OpenAlex metadata.

Limitations

Limitations are not available in the OpenAlex metadata.

Applications

Application details are not available in the OpenAlex metadata.

Available abstract

An investigation was conducted in the NACA Lewis 10- by 10-foot supersonic wind tunnel to evaluate the performance of three burner configurations in a 16-inch ram jet with gaseous hydrogen as fuel. Data were obtained over a fuel-air-ratio range from 0.0030 to 0.0260 (stoichiometric = 0.0292) at a free-stream Mach number of 3.0 and 0 degree angle of attack. The exit nozzle-throat area ratios employed were 0.60 and 0.75.

Key concepts: Mach number, Combustor, Nozzle, Supersonic speed, Jet (fluid), Jet fuel, Hydrogen, Materials science

Related papers

Related paper 1Related paper 2Related paper 3
Back to paper searchBrowse research topicsOriginal source
Combustor performance of a 16-inch ram jet using gaseous hydrogen as fuel at Mach number 3.0 — Research Paper | ScholarLens