Hypersonic Shock Wave Interactions on a V-Shaped Blunt Leading Edge

Xiao, Fengshou; Li, Zhufei; Zhang, Zhiyu; Zhu, Yujian; Yang, Jiming

doi:10.2514/1.j055915

Cited by 24 publications

(16 citation statements)

References 25 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Figure 7 shows how the surface heat flux is affected by the leading-edge bluntness r, in which the symbols denote the numerical results of the stagnation-point heat flux (red dots) and the peak values in the surface heat flux qmax (blue triangles) of the leading edge, and the curve represents the classical prediction based on the Fay and Riddell's theory. It is well known from Fay and Riddell's theory that the stagnation heat flux scales inversely with the square root of the leading-edge bluntness r. The present results agrees fairly well if the bluntness r is small enough (region A), under a given radius of the crotch R. However, if r is increased beyond a certain level, the peak heat flux starts to climb up again remarkably, which is comparable to that of the well-known type IV shock interactions [9]. This finding needs to be emphasized since it is opposite to our conventional concept of heat protection.…”

Section: Fig 6 Schlieren Images Of Various Interaction Types [8]supporting

confidence: 86%

“…Fig. 7 Surface heat flux at different leading edge bluntness conditions [9] Fig. 8 Three-dimensional interference around VsBLE [10] Therefore, it should be pointed out that the variables β, r, and R, etc., could be well arranged or optimized so that not only the peak heat flux can be reduced remarkably, but also the flow field can be much more regularly organized at the same time.…”

Section: Fig 6 Schlieren Images Of Various Interaction Types [8]mentioning

confidence: 99%

See 1 more Smart Citation

Simplified Model Researches for Understanding the Complex Shock Interactions in Hypersonic Inlet Flow

Yang¹

2019

Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019)

Self Cite

View full text Add to dashboard Cite

The paper presents some progresses of the shock wave interaction studies in author's group, with the application background of complex hypersonic inlet flow, particularly with a focus on the characterization of an inward-turning inlet flow. We start with a report of several experimental efforts, which attempted to visualize the flow features hidden in an inlet. Then the major topic is concentrated on the cowl lip, namely a simplified "V" shaped blunt leading edge, about which a severe shock interaction is discussed that is comparable to the well-known type IV interaction in the sense of peak pressure and heat flux. Another discussion is about the behaviors of a near-axisymmetric converging shock wave, which is picked up as a candidate to exhibit some typical characteristics in an inwardturning inlet that differ remarkably from the case of a 2D inlet.

show abstract

Section: Fig 6 Schlieren Images Of Various Interaction Types [8]supporting

confidence: 86%

Section: Fig 6 Schlieren Images Of Various Interaction Types [8]mentioning

confidence: 99%

Simplified Model Researches for Understanding the Complex Shock Interactions in Hypersonic Inlet Flow

Yang¹

2019

Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019)

Self Cite

View full text Add to dashboard Cite

show abstract

“…With the development of hypersonic airbreathing vehicles (see figure 1a), a V-shaped blunt leading edge (VSBLE) (see figure 1b) of the inlet has been noted by researchers (Malo-Molina et al 2010). Xiao et al (2018) first extracted the VSBLE configuration from vehicles and defined the main geometric parameters including the half-span angle β, the leading-edge radius r and the crotch radius R. Based on this model, Li et al (2019) and Wang et al (2018) studied the pressure-heat flux correlation and unsteady shock oscillation around the VSBLE. Furthermore, Zhang et al (2019aZhang et al ( , 2021a combined experiments, numerical simulations and theoretical analysis to explore the shock structures around the VSBLE with a wide range of geometric parameters.…”

Section: Introductionmentioning

confidence: 97%

“…Xiao et al. (2018) first extracted the VSBLE configuration from vehicles and defined the main geometric parameters including the half-span angle β , the leading-edge radius r and the crotch radius R . Based on this model, Li et al.…”

Section: Introductionmentioning

confidence: 99%

Modelling and shock control for a V-shaped blunt leading edge

et al. 2023

View full text Add to dashboard Cite

Hypersonic flow on a V-shaped blunt leading edge (VSBLE) at Mach 12 is numerically investigated. A series of self-induced shock–shock interactions and shock wave/boundary layer interactions (SWBLIs) cause extremely high heat flux peaks on the crotch of the VSBLE. Based on these shock structures, a simplified model that divides the flow field into inviscid and viscous areas is constructed. This model can quickly solve the shock interactions and predict the heating/pressure peaks with high accuracy. Furthermore, a shock control bump (SCB) is placed on the SWBLI region to split the strong incident shock into a weaker multi-wave system. The mechanism study of the SCB shows that the inviscid effect significantly reduces the heating/pressure peaks, and the viscous effect suppresses the SWBLI-induced separation. Finally, a VSBLE with SCBs is numerically investigated. The heat flux peak is reduced by 66 % compared to that without the SCBs. The robustness of the SCB under various working conditions is also evaluated. This paper provides an idea for the simplified solution of complex shock interactions and extends the application of the SCB as a thermal protection device in hypersonic flow for the first time.

show abstract

“…Recently, there has been a growing interest in shock interactions occurring on a V-shaped blunt leading edge (VBLE) (Xiao et al. 2018; Zhang et al. 2019; Zhang, Li & Yang 2021), which is typically observed in a hypersonic inward-turning inlet (You 2011; Gollan & Smart 2013; Bisek 2016).…”

Section: Introductionmentioning

confidence: 99%

Mach reflection of three-dimensional curved shock waves on V-shaped blunt leading edges

Zhang,

Cheng,

Shi

et al. 2023

J. Fluid Mech.

View full text Add to dashboard Cite

Theoretical investigation of the primary Mach reflection (MR) configuration on V-shaped blunt leading edges (VBLEs) forms the focus of this study. By ignoring the secondary interactions, a theoretical method based on a simplified form of the continuity relation is developed to predict the shock configurations, including the detached shock, the Mach stem, the transmitted shock and the triple point. The comparison of the theoretical results with both numerical and previous experimental results shows the reliability of the theoretical approach in predicting shock structures across a wide range of free stream and geometric parameters. The theoretical model provides a detailed comprehension of the occurrence mechanism of inverse MRs on VBLEs and the influence of the free stream and geometric parameters on primary MR configurations. Along with the primary MR configuration, the curved shock or compression waves generated by the crotch are solved and offer insight into the transition from the MR to the regular reflection from the same family (sRR). The increase of the ratio $R/r$ and the free stream Mach number $M_0$ appears to facilitate the transition, while the effect of the half-span angle $\beta$ is non-monotonic. The predicted shock positions allow for the identification of the transition boundary between the primary MR and sRR. It is found that $R/r$ below a threshold (for a set $M_0$ value) produces MR, irrespective of $\beta$ . If this threshold is exceeded, the configuration can transition from the primary MR to sRR and then back to the primary MR as $\beta$ increases.

show abstract

Hypersonic Shock Wave Interactions on a V-Shaped Blunt Leading Edge

Cited by 24 publications

References 25 publications

Simplified Model Researches for Understanding the Complex Shock Interactions in Hypersonic Inlet Flow

Simplified Model Researches for Understanding the Complex Shock Interactions in Hypersonic Inlet Flow

Modelling and shock control for a V-shaped blunt leading edge

Mach reflection of three-dimensional curved shock waves on V-shaped blunt leading edges

Contact Info

Product

Resources

About