Turbulent flame compressibility criterion for scramjet unstart and transition
A new criterion predicting the onset of scramjet unstart is proposed. The source of unstart is hypothesized to stem from the turbulent compressible flame choking altering the optimal thermal choking design location or geometry of a scramjet combustor for heat release. This criterion is useful for assessing scramjet unstart and engine tuning for optimal heat release for ideal expansion and engine performance.
Authors
- Justin D. Sprunger
- Kareem A. Ahmed (ORCID: https://orcid.org/0000-0003-3204-0165)
- Rachel Hytovick (ORCID: https://orcid.org/0000-0002-4605-0543)
- Jonathan Sosa
- Andrew J. La Sorsa
Institutions
- University of Central Florida (US)
- United States Naval Research Laboratory (US)
Publication Details
- Journal
- Combustion and Flame
- Published
- 2025-02-12
- DOI
- https://doi.org/10.1016/j.combustflame.2025.114044
- Citations
- 5
- Primary Topic
- Computational Fluid Dynamics and Aerodynamics
- Type
- article
- Field-Weighted Citation Impact
- 6.67
Funders
- Office of Naval Research
- Air Force Office of Scientific Research