Theoretical, numerical and experimental study of hypersonic boundary layer transition: Blunt circular cone

Chen, Jianqiang; Yi, Shihe; Li, Xinliang; Han, Guilai; Zhang, Yifeng; Yang, Qiang; Yuan, Xianxu

doi:10.1016/j.applthermaleng.2021.116931

Cited by 15 publications

(4 citation statements)

References 74 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The modern applications of boundary-layer theory are the calculation of friction drag of bodies e.g. a ship (Schlichting and Gersten 2016), behavior of turbulence (Mahrt 2014), Hypersonic boundary layer transition (Chen et al 2021), nanofluids boundary layer flow (Awati, Goravar, and Wakif 2022;Gangadhar et al 2020) and also magnetohydrodynamics (MHD) boundary layer flow of nanofluids analysis, especially regarding thermodynamic and heat transfer (Khashi'ie, Arifin, and Pop 2022;Rashid, Sagheer, and Hussain 2019;Reddy and Sreedevi 2021;Rashad, Chamkha, and Modather 2013). Similarity solutions of boundary layer flow are possible for some conditions (Aziz 2009).…”

Section: Introductionmentioning

confidence: 99%

Numerical Solution of Non-Similar Boundary-Layer Flow Over a Cylinder

Rezaee,

Houshmand

2023

JSSCM

View full text Add to dashboard Cite

This paper presents Ð° numerical solution of a non-similar two-dimensional boundary-layer flow over a cylinder. The assumptions and related two-dimensional flow equations are presented. The fourth-order Runge-Kutta method with the backward differentiation formula (BDF) method to separation point is implemented in the numerical solution using MATLAB software. Numerical solution results are compared with well-known analytic solutions. Shear stress diagram, friction ratio based on Î¸ and x, and output results are illustrated. The results of numerical solution demonstrate good consistency with analytic solutions.

show abstract

Section: Introductionmentioning

confidence: 99%

Numerical Solution of Non-Similar Boundary-Layer Flow Over a Cylinder

Rezaee,

Houshmand

2023

JSSCM

View full text Add to dashboard Cite

show abstract

“…Hypersonic boundary layer (HBL) transition has a crucial impact on the performance of high-speed flying vehicles and has been the focus of many theoretical, experimental and numerical studies during the past several decades [1]. Compared to low-speed flows, HBL transition is subjected to more instability mechanisms and more transitioninfluential factors [2,3].…”

Section: Introductionmentioning

confidence: 99%

“…Since nearly all transition models include a correlation equation to define the transition onset location [6,7], which is poorly predicted in general, the existing models usually give insufficient and even undetermined prediction accuracies [8,9]. Furthermore, HBLs are generally governed by different instability mechanisms on different surface areas [1,10,11], which results in enormous complexities in modeling and simulating HBL transitions [12,13]. The status calls for a reflection: whether one should always rely on a correct description of the transition mechanism for the foundation of a transition model, or perhaps might discover a universal principle governing transitional boundary layers, and work out a more efficient transition model.…”

Section: Introductionmentioning

confidence: 99%

A symmetry-based length model for characterizing the hypersonic boundary layer transition on a slender cone at moderate incidence

Wei

ZHENG

et al. 2022

Adv. Aerodyn.

View full text Add to dashboard Cite

The hypersonic boundary layer (HBL) transition on a slender cone at moderate incidence is studied via a symmetry-based length model: the SED-SL model. The SED-SL specifies an analytic stress length function (which defines the eddy viscosity) describing a physically sound two-dimensional multi-regime structure of transitional boundary layer. Previous studies showed accurate predictions, especially on the drag coefficient, by the SED-SL for airfoil flows at different subsonic Mach numbers, Reynolds numbers and angles of attack. Here, the SED-SL is extended to compute the hypersonic heat transfer on a 7 ∘ half-angle straight cone at Mach numbers 6 and 7 and angles of attack from 0 ∘ to 6 ∘. It is shown that a proper setting of the multi-regime structure with three parameters (i.e. a transition center, an after-transition near-wall eddy length, and a transition width quantifying transition overshoot) yields an accurate description of the surface heat fluxes measured in wind tunnels. Uniformly good agreements between simulations and measurements are obtained from windward to leeward side of the cone, implying the validity of the multi-regime description of the transition independent of instability mechanisms. It is concluded that a unified description for the HBL transition of cone is found, and might offer a basis for developing a new transition model that is simultaneously of computational simplicity, sound physics and greater accuracy.

show abstract

“…As one of the key issues in the design of hypersonic vehicles, hypersonic boundary layer transition control is always a research hotspot in the aerospace field [1][2][3][4]. The huge difference between the laminar and turbulent flow states caused by the boundary layer transition affects local aerodynamic and aerothermal performance, which seriously affects the performance of aircraft [5].…”

Section: Introductionmentioning

confidence: 99%

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Yang¹,

Liang²,

Guo³

et al. 2022

Plasma Sci. Technol.

View full text Add to dashboard Cite

Effective control of hypersonic transition is essential. In order to avoid affecting the structural profile of the aircraft, reduce power consumption and electromagnetic interference, the experiment of low-frequency surface arc plasma disturbance to promote hypersonic transition was carried out in the Φ0.25m double-throat Ludwieg tube wind tunnel of Huazhong University of Science and Technology. The contacting PCB sensors and non-contact focused laser differential interferometry testing technology (FLDI) are used in combination. Experimental results show that the low-frequency surface arc plasma actuation has obvious stimulation effects on the second mode unstable wave and can promote boundary layer transition by changing the spectral characteristics of the second mode unstable wave. At the same time, the plasma actuation can promote the energy exchange between the second mode unstable wave and other unstable waves. Finally, the corresponding control mechanism is discussed preliminarily.

show abstract

Theoretical, numerical and experimental study of hypersonic boundary layer transition: Blunt circular cone

Cited by 15 publications

References 74 publications

Numerical Solution of Non-Similar Boundary-Layer Flow Over a Cylinder

Numerical Solution of Non-Similar Boundary-Layer Flow Over a Cylinder

A symmetry-based length model for characterizing the hypersonic boundary layer transition on a slender cone at moderate incidence

Experimental study on surface arc plasma actuation-based hypersonic boundary layer transition flow control

Contact Info

Product

Resources

About