Mixing and combustion of supersonic reacting flows are currently under investigation for scramjet engines. Experimental results at NASA-Langley RC with single-jet hydrogen injection at Mach 2.5 in a Mach 2 airstreams showed combustion taking place in a very short lenght: this indicates that supersonic combustion may indeed be very fast. Numerical simulations of the same test case have also done using LES and the subgrid scale model, ISCM, developed purposely for supersonic combustion. This model accounts for the effects of compressibility on reaction rate and on mixing. Numerical simulations indicate that the flame is unsteady: it anchors at about 15 cm from the injector, develops downstream and lifts off. Periodical ignition and quenching have been investigated by means of frequency analysis.
|Publication status||Published - 2007|
|Event||45th AIAA Aerospace Sciences Meeting 2007 - , United States|
Duration: 1 Jan 2007 → …
|Conference||45th AIAA Aerospace Sciences Meeting 2007|
|Period||1/1/07 → …|
All Science Journal Classification (ASJC) codes
- Space and Planetary Science
- Aerospace Engineering
Ingenito, A., Bruno, C., Giacomazzi, E., & Steelant, J. (2007). Advance in supersonic combustion modelling and simulations. Paper presented at 45th AIAA Aerospace Sciences Meeting 2007, United States.