Study of multiple solution phenomenon for hypersonic air inlet

Tang, Xiao; Fan, Xiaoqiang; Xiong, Bing; Chen, Lei; Chen, Jingfan

doi:10.1016/j.ast.2023.108236

Cited by 8 publications

(4 citation statements)

References 50 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Equation ( 1) is the conservation form of compressible Navier-Stokes equations. The calculation object was perfect gas (air) [9,13,15,48], and the fluid's viscosity was computed using the Sutherland equation. Since the calculation problem concerned compressible flow, and in order to address to the calculation accuracy and efficiency, a density-based solver conducted via an implicit time integration method and second-order upwind ROE difference scheme was chosen to solve the complex problem.…”

Section: Computational Fluid Dynamics (Cfds) Methodsmentioning

confidence: 99%

“…The previous discovery shows that there are three distinct types of unstart modes in some hypersonic inlets [48]. They are the flow mode of large separation on body (LSB), flow mode of small separation on body (SSB), and flow mode of dual separations on both body and lip (DSBL).…”

Section: Three Distinct Types Of Unstart Modementioning

confidence: 99%

“…Because of complex flow in hypersonic inlets where intense shock boundary-layer interference and significant three-dimensional effects exist, multiple unstart modes inevitably occur. For example, in a recent study, three distinct types of unstart modes which are not related to overrating were discovered in a hypersonic inlet [48]: the flow mode of large separation on body (LSB), small separation on body (SSB), and dual separations on both body and lip (DSBL). These are described in detail in Section 3.1.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Tang,

Xiong,

Fan

et al. 2023

Applied Sciences

Self Cite

View full text Add to dashboard Cite

Intense shock boundary-layer interaction may lead to multiple unstart modes existing in a hypersonic inlet. Thus, self-start problems become complex and cannot be explained using the classical double-solution theory of air inlet. The essence of the self-start process of a hypersonic inlet is the vanishment of separations near or in the inlet. To clarify self-start characteristics, experiments were conducted on three distinct types of unstart mode: the flow mode of small separation on body (SSB), large separation on body (LSB), and dual separations on both body and lip (DSBL); researchers recently discovered these as the unstart modes of hypersonic inlet. The results from the current experiment are as follows: (1) The SSB vanishes by raising the angle of attack (alpha). Before the vanishing point is reached, there is a dwindling process for this separation. (2) The LSB vanishes through acceleration or a decreasing alpha. (3) DSBL are difficult to vanish directly, which results in poor self-start performance. However, the DSBL flow mode may convert to LSB unstart form—which is easier to self-start—by decreasing the alpha. The Flow Field Reconstruction Method was designed to improve the self-start of the DSBL flow mode, and it was validated through experiments. Analysis of the flow mechanism revealed the reason for the poor self-start performance of the DSBL unstart mode: large-scale separation on the lip side cannot be promoted to vanish through broadwise spillage due to the resistance of sideboards. The results of this study could greatly enrich the existing theory of start problems for hypersonic inlets.

show abstract

Section: Computational Fluid Dynamics (Cfds) Methodsmentioning

confidence: 99%

Section: Three Distinct Types Of Unstart Modementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Tang,

Xiong,

Fan

et al. 2023

Applied Sciences

Self Cite

View full text Add to dashboard Cite

show abstract

“…The inlet as an important aerodynamic assembly of a hypersonic vehicle mounted at the forefront of hypersonic vehicle, which has a significant impact on the aerodynamic characteristics, structural weights, stealth performances and so on. And inlet has direct impact on the working efficiency and envelope of the propulsion system (Ma et al 2024;Tang et al 2024;Zhang et al 2014), such as, capturing and adjusting mass flow rate of gas, transforming and utilizing kinetic energy of gas, controlling gas velocity, enhancing flow uniformity, isolating the disturbances of upstream and downstream. Accordingly, the inlet performances are mainly characterized and evaluated by several corresponding parameters, including the mass flow rate, the total pressure recovery coefficient, the skin friction coefficient and the outlet Mach number, etc.…”

Section: Introductionmentioning

confidence: 99%

Numerical analysis on the MHD flow control of the hypersonic vehicle inlet

Li,

Huang,

Zhu

2024

Preprint

View full text Add to dashboard Cite

Under the assumption of the low magnetic Reynolds number, the coupled model of the turbulent flow field and the electromagnetic field is established to simulate the flow characteristics of Weakly Ionized Gas (WIG) in the inlet under the MHD (Magnetohydrodynamic) effect. Results show that WIG has more active thermodynamic properties than that of air in inlet. Specifically, at the throat, the thermal conductivity of WIG is augmented by 1.64 times compared to that of air. For the inlet with an MHD acceleration zone, the separation shock waves will be fallen on the third ramp and converted into the reattachment shock waves here. And the separation bubbles generated by the reattachment shock waves are weakened due to the multiple reflections before entering the isolator, hence, the wall pressure and the skin friction coefficient have a decrease in the isolator. Nevertheless, in the inlet with an MHD deceleration zone, the separation shock waves will be fallen precisely at the throat under the effect of the countercurrent Lorentz force, so that the separation shock waves are directly transformed into reattachment shock waves at the throat and all reflected into the isolator, which leads to the peak manifestation of the wall pressure and the skin friction coefficient in the isolator.

show abstract

Hysteresis of oscillatory airflow in a supersonic intake model

Kuzmin

2024

View full text Add to dashboard Cite

Study of multiple solution phenomenon for hypersonic air inlet

Cited by 8 publications

References 50 publications

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Self-Start Characteristics of Hypersonic Inlet When Multiple Unstart Modes Exist

Numerical analysis on the MHD flow control of the hypersonic vehicle inlet

Hysteresis of oscillatory airflow in a supersonic intake model

Contact Info

Product

Resources

About