Experimental supersonic combustion research at NASA Langley

TLDR

NASA Langley has conducted experimental supersonic combustion research for hypersonic airbreathing propulsion since the mid‑1960s. The paper reviews LaRC’s experimental supersonic combustion research from the late 1980s through the NASP and Hyper‑X programs. The research involved extensive experimental studies of fuel injection, mixing, and combustion in supersonic flows, including nearly 2,500 tests of 15 scramjet models and high‑Mach tests up to Mach 17 in expansion‑tube facilities. The work produced scramjet combustor design methods, ground‑test techniques, and data‑analysis procedures that have advanced the NASP and Hyper‑X programs.

Abstract

Experimental supersonic combustion research related to hypersonic airbreathing propulsion has been actively underway at NASA Langley Research Center (LaRC) since the mid-1960's. This research involved experimental investigations of fuel injection, mixing, and combustion in supersonic flows and numerous tests of scramjet engine flowpaths in LaRC test facilities simulating flight from Mach 4 to 8. Out of this research effort has come scramjet combustor design methodologies, ground test techniques, and data analysis procedures. These technologies have progressed steadily in support of the National Aero-Space Plane (NASP) program and the current Hyper-X flight demonstration program. During NASP nearly 2500 tests of 15 scramjet engine models were conducted in LaRC facilities. In addition, research supporting the engine flowpath design investigated ways to enhance mixing, improve and apply nonintrusive diagnostics, and address facility operation. Tests of scramjet combustor operation at conditions simulating hypersonic flight at Mach numbers up to 17 also have been performed in an expansion tube pulse facility. This paper presents a review of the LaRC experimental supersonic combustion research efforts since the late 1980's, during the NASP program, and into the Hyper-X Program.