Close-collaborative experimental and computational study of a dual-mode scramjet combustor

Robert D. Rockwell, Christopher P. Goyne, Brian E. Rice, Benjamin J. Tatman, Chad Smith, Toshinori Kouchi, James C. McDaniel, Jesse A. Fulton, Jack R. Edwards

Research output: Contribution to conferencePaperpeer-review

17 Citations (Scopus)


Advanced computational models of hypersonic air-breathing combustion processes are being developed to better understand and predict the complex flows within a dual-mode scramjet combustor. However, the accuracy of these models can only be quantified through comparison to experimental databases. Moreover, the quality of computational results is dependent on accurate and detailed knowledge of the combustor inflow and boundary conditions. Toward those ends, this paper describes the initial results of a unique, close collaboration of experimental and computational approaches. Detailed computational fluid dynamics (CFD) and finite element thermal-structural analyses (FEA) have been performed throughout the design and implementation of a direct-connect scramjet combustor operating at steady state during long duration testing on the order of an hour or more. The test-section hardware has been designed to provide numerous access points for optical laser diagnostic measurements. Measurement locations include the inflow plane to the scramjet combustor as well as several locations downstream of the fuel injector. In addition, static wall pressures and temperatures are measured at numerous points along the fuel injector side of the scramjet flowpath. Initial CFD calculations were used to generate detailed thermal boundary conditions that were then applied to a non-linear, thermal-structural finite element model of the test-section. The calculated temperatures and thermal deformations are evaluated and validated against experimental measurements. Significant results described in this paper include experimentally measured static wall pressure and temperature data, Stereoscopic Particle Image Velocimetry (SPIV) and focused schlieren imaging. Validated finite element calculations of temperature in the test-section hardware, and temperature maps of the flowpath boundaries are also presented. CFD results are discussed in a separate paper.

Original languageEnglish
Publication statusPublished - Jun 20 2012
Externally publishedYes
Event50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition - Nashville, TN, United States
Duration: Jan 9 2012Jan 12 2012


Other50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition
Country/TerritoryUnited States
CityNashville, TN

ASJC Scopus subject areas

  • Aerospace Engineering


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