High fidelity numerical simulation of hypersonic three dimensional shock-boundary layer interactions
Abstract
We propose to carry out high fidelity simulations (DNS-LES) of three dimensional shock boundary layer interactions in the supersonic to hypersonic flow regime, with special reference to the representative case of the shock generated by a conical object made to interact with a fully developed boundary layer on a flat wall. This problem has direct practical relevance in aerospace technology as interactions of this kind frequently occur both in external flows, in the case of interference between aircraft appendices-boosters and main body, as well as internal flows, as in the case of air intakes. Besides its obvious technological relevance, numerical study of three dimensional shock-boundary layer interactions is also instrumental to the development of improved wall models for LES, which should be capable of accurately incorporating the effect of cross stream pressure gradient. Numerical simulations of turbulent wall bounded flows will will be carried out for different wall conditions, namely adiabatic and cooled, with the additional goal of understanding and predicting deviations of the flow statistics from supposed universality as encapsulated in the classical Morkovin’s hypothesis.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 14, 2022
- Source ID
- FA95501917029
Entities
People
- Sergio Pirozzoli
Organizations
- Air Force Office of Scientific Research
- Sapienza University of Rome
- United States Air Force