Numerical Study on Supersonic Inlet Buzz Under Various Throttling Conditions and Fluid-Structure Interaction

Hong, Wooram; Kim, Chongam

doi:10.2514/6.2011-3967

Cited by 10 publications

(5 citation statements)

References 13 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As seen, up to now no reliable prediction method of intake buzz has been developed through the analytical investigations. Therefore, numerical [9,[17][18][19][20][21][22][23][24][25][26][27][28][29][30] or experimental [8,13,23,25,27,[31][32][33][34][35][36][37][38][39][40][41][42][43][44] methods are often used to study the buzz onset as well as its frequency and amplitude for various flow conditions. It seems that the work done by Trapier et al [18] is the most complete study among the numerical investigations because the flow separation is the key phenomenon in the buzz onset according to the Ferri [5] and Dailey [6] criteria, and to the authors' knowledge, this study is the only numerical investigation that uses the large-eddy simulation approach (detached-eddy simulation turbulence model) and three-dimensional grid to study buzz.…”

mentioning

confidence: 99%

Buzz Cycle Description in an Axisymmetric Mixed-Compression Air Intake

Soltani

Sepahi-Younsi

2016

AIAA Journal

View full text Add to dashboard Cite

mentioning

confidence: 99%

Buzz Cycle Description in an Axisymmetric Mixed-Compression Air Intake

Soltani

Sepahi-Younsi

2016

AIAA Journal

View full text Add to dashboard Cite

“…Figure 4a shows the evolution of total pressure recovery and internal compression ratio (ICR) with varying cowl internal angle θ c , in which ICR is defined as the area ratio of profile 2 to profile 3, as shown in Figure 1. Generally, a larger ICR tends to lead to enhanced compression ability but more easily allows inlet unstart [5,26], which results in serious damages for the whole engine [27][28][29][30][31]. It is clearly seen that, the variation curves of total pressure recovery and ICR are nearly overlapped in Figure 4a, showing a non-monotonic variation with θ c and reaching a peak value of about 77.8% for total pressure recovery and 2.75 for ICR at θ c = 10.53 • .…”

Section: The Influence Of the Limit Of Cowl Internal Anglementioning

confidence: 99%

Lagrange Optimization of Shock Waves for Two-Dimensional Hypersonic Inlet with Geometric Constraints

Yue

et al. 2022

Aerospace

View full text Add to dashboard Cite

The present paper focuses on the Lagrange optimization of shock waves for a two-dimensional hypersonic inlet by limiting the cowl internal angle and inlet length. The results indicate the significant influences of geometric constraints on the configuration of shock waves and performances of an inlet. Specifically, the cowl internal angle mainly affects the internal compression section; the inlet length affects both the internal and external compression sections where the intensity of internal and external compression shock waves shows a deviation of equal. In addition, the performances of optimized inlets at off-design points are further numerically simulated. A prominent discovery is that a longer inlet favors a higher total pressure recovery at the positive AOA; conversely, a shorter inlet can increase the total pressure recovery at the negative AOA.

show abstract

“…Once throttling occurred, flow patterns were dramatically altered by the detachment vortex bubbles that formed on the external compression wall and inside the neck. Although the TR decreased, the dominant pressure disturbance rate increased, and the disturbance trend became more irregular, although its amplitude decreased in concentration [29].…”

Section: Introductionmentioning

confidence: 96%

Assessing the Performance of Hypersonic Inlets by Applying a Heat Source with the Throttling Effect

et al. 2022

View full text Add to dashboard Cite

Utilization of a heat source to regulate the shock wave–boundary layer interaction (SWBLI) of hypersonic inlets during throttling was computationally investigated. A plug was installed at the intake isolator’s exit, which caused throttling. The location of the heat source was established by analysing the interaction of the shockwave from the compression ramp and the contact spot of the shockwave with that of the inlet cowl. Shockwave interaction inside the isolator was investigated using steady and transient cases. The present computational work was validated using previous experimental work. The flow distortion (FD) and total pressure recovery (TPR) of the inflows were also studied. We found that varying the size and power of the heat source influenced the shockwaves that originated around it and affected the SWBLI within the isolator. This influenced most of the performance measures. As a result, the TPR increased and the FD decreased when the heat source was applied. Thus, the use of a heat source for flow control was found to influence the performance of hypersonic intakes.

show abstract

Numerical Study on Supersonic Inlet Buzz Under Various Throttling Conditions and Fluid-Structure Interaction

Cited by 10 publications

References 13 publications

Buzz Cycle Description in an Axisymmetric Mixed-Compression Air Intake

Buzz Cycle Description in an Axisymmetric Mixed-Compression Air Intake

Lagrange Optimization of Shock Waves for Two-Dimensional Hypersonic Inlet with Geometric Constraints

Assessing the Performance of Hypersonic Inlets by Applying a Heat Source with the Throttling Effect

Contact Info

Product

Resources

About