Hypersonic flow over a two-dimensional compression corner with Mach number of 7.7 and unit Reynolds 4.2 × 10 6 m ?1 is numerically investigated. Special emphasis given to the onset global instability respect three-dimensional perturbations. Global stability analysis performed for various ramp angles wall temperatures. It found that shock-induced separated system becomes unstable when angle beyo...

Aerothermoelastic fluid–structure interaction (FSI) is a crucial problem in the design of supersonic and hypersonic vehicles, but modeling capabilities are many cases quite limited. Insufficient treatment FSI can limit options or lead to damage loss vehicles. To improve understanding such problems, we conducted experiments with thin panels flow wind tunnel H2K at DLR, Cologne, where both therma...

The hypersonic effect is a phenomenon in which sounds containing significant quantities of non-stationary high-frequency components (HFCs) above the human audible range (max. 20 kHz) activate the midbrain and diencephalon and evoke various physiological, psychological and behavioral responses. Yet important issues remain unverified, especially the relationship existing between the frequency of ...

This paper examines the use of a hypersonic bi-directional flying wing concept for use in a high efficiency hypersonic system. The bi-directional flying wing concept consists of a symmetric planform which enables flight to occur at two different geometric configurations. The subsonic configuration would have a high aspect ratio and a low sweep. The aircraft would then rotate 90 degrees and ente...

Hypersonic flow over a two-dimensional compression corner is investigated using computational fluid dynamics and global resolvent analysis in this study, which continuation of the work done by Hao et al. ( J . Fluid Mech. , vol. 919, 2021, p. A4). The same baseline free-stream conditions with Mach number 7.7 unit Reynolds 4.2 × 10 6 m −1 are considered. ramp angles range from 0° (equivalent to ...

In this work, the stability of hypersonic flow over a curved compression ramp is studied using several analysis tools and direct numerical simulations (DNS). The free-stream Mach number unit Reynolds are 7.7 $4.2 \times 10^6$ m $^{-1}$ , respectively. Corner rounding considered to alter separation bubble so as suppress intrinsic instability compression-ramp flow. variation confirmed by global a...

A preliminary hybrid particle-continuum computational framework for simulating hypersonic interacting flows is proposed. The framework consists of the direct simulation Monte Carlo-Information Preservation (DSMC-IP) method coupled with a NavierStokes solver. Since the DSMC-IP method provides the macroscopic information in each time step, determination of the continuum fluxes across the interfac...