Two-dimensional interaction between an incident shock and a turbulent boundary layer in the presence of an entropy layer

Borovoi, V. Ya.; Егоров, И. В.; Noev, A. Yu.; Skuratov, A. S.; Struminskaya, I. V.

doi:10.1134/s0015462811060093

Cited by 8 publications

(2 citation statements)

References 19 publications

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“…This study showed that Equal Length blunting Manner (ELM) is the most optimal which ensures the minimal total pressure loss, the lowest cowl drag, maximum mass-capture and the minimal aeroheating. The concept of blunt leading edge based SWBLI control has also been demonstrated by Borovoi et al (2011) through their experimental studies. In this work two dimensional interaction between an incident shock and a turbulent boundary layer in the presence of an entropy layer was experimentally investigated by varying plate bluntness and the incident shock position.…”

Section: Introductionmentioning

confidence: 96%

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

John

Senthilkumar

2018

JAFM

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This paper discusses the performance enhancement of supersonic air intake model through the implementation of blunted leading edge to the cowl lip section of the model. A supersonic air intake model with sharp cowl leading edge is initially considered to numerically investigate its performance. Mach 3, supersonic intake flow through the base model has been simulated using commercial CFD package Ansys Fluent-15. Comparison of numerical predictions and experimental measurements is presented to demonstrate the correctness and accuracy of numerical frame work followed in the present study. Higher order spatial accuracy of the solver along with suitably refined mesh helped in accurate capturing of the flow field. Modification to the cowl lip is proposed as an effective method to improve the performance of the supersonic air intake. Two different blunted cowl leading edge geometries were investigated to identify the possible enhancement in performance parameters. Improvement in mass capture and combustion stability attained through the use of forward shifted blunt cowl leading edge is presented. It is also revealed through the present study that the blunt cowl leading edge can reduce the intensity of shock wave boundary layer interaction occurring at the isolator entry section. Deviation in total pressure recovery and flow distortion observed with different supersonic air intake models are also discussed with reasons for the same. This study demonstrates the scope of overall improvement in scramjet engine performance through the use of suitably positioned blunt cowl leading edge.

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Section: Introductionmentioning

confidence: 96%

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

John

Senthilkumar

2018

JAFM

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“… Calculation process of numerical evaluation of flow conditions in sections of high-speed ground test facilities and comparison with experimental data to understand the physics of hypersonic interactions in the facility sections [1 -8] and hypervelocity flow interactions over sharp and blunt bodies with different incoming flow conditions [9 -11];  Ground test measurements for aerothermal and thermochemical effects on spherical capsule geometries with different gases for re-entry applications [12 -15];  Velocity/altitude simulation for scramjet engine testing at different flight conditions [4,16];  The flow structure and heat exchange in the zone of interference between an inclined shock and the surface of a flat plate [17] and blunt bodies [18,19];  Investigations of leading edge bluntness influence on flow in air-inlet model with rectangular cross-section [20,21];  Transition between regular and Mach reflections of steady shock waves and its influence on flow characteristics [22,23]. In our previous works, the models of flat inlet sections were experimentally investigated with the use of the laboratorial hypersonic aerodynamic shock tube (HAST) [24][25][26][27][28].…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical study of supersonic flow over two blunted wedges

Kotov

Ruleva

Solodovnikov

et al. 2017

J. Phys.: Conf. Ser.

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Abstract. Shock-wave experiments with aerodynamic primitives in the form of a half wedge/double wedge with blunt edges are performed. Experimental studies were conducted using models, which are located at the exit of the supersonic nozzle of the hypersonic aerodynamic shock tube (HAST). Schlieren fragments of shock-wave formation over wedges were experimentally obtained. Calculations of the shock wave interactions over models carried out with the use of the authors' computer codes. The predicted results and their comparison with experiment showed a satisfactory agreement. IntroductionShock-wave interactions are characteristic feature of high-speed flows near the various elements of constructions of high-speed vehicles. The variety of arising shock-wave configurations makes the task of experimental and theoretical study very complex. However, the practical importance of the problem of the understanding of the mechanisms of shock-wave interaction between themselves and with surfaces of the vehicles puts this problem in a number of high priorities of experimental, theoretical and computational aerodynamics and physical mechanics.In recent years experimental and computational studies [1 -23] have allowed to classify the main problems, the study of which is of greatest interest and at the same time, the greatest difficulties. Among them: Calculation process of numerical evaluation of flow conditions in sections of high-speed ground test facilities and comparison with experimental data to understand the physics of hypersonic interactions in the facility sections [1 -8] and hypervelocity flow interactions over sharp and blunt bodies with different incoming flow conditions [9 -11];  Ground test measurements for aerothermal and thermochemical effects on spherical capsule geometries with different gases for re-entry applications [12 -15];  Velocity/altitude simulation for scramjet engine testing at different flight conditions [4,16];  The flow structure and heat exchange in the zone of interference between an inclined shock and the surface of a flat plate [17] and blunt bodies [18,19];  Investigations of leading edge bluntness influence on flow in air-inlet model with rectangular cross-section [20,21];  Transition between regular and Mach reflections of steady shock waves and its influence on flow characteristics [22,23]. In our previous works, the models of flat inlet sections were experimentally investigated with the use of the laboratorial hypersonic aerodynamic shock tube (HAST) [24][25][26][27][28]. Along with the

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Influence of leading edge bluntness on hypersonic flow in a generic internal-compression inlet

Borovoy

Егоров

Mosharov

et al. 2015

Progress in Flight Physics – Volume 7

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Flow and heat transfer inside a generic inlet are investigated experimentally. The cross section of the inlet is rectangular. The inlet is installed on a §at plat at a signi¦cant distance from the leading edge. The experiments are performed in TsAGI wind tunnel UT-1M working in the Ludwieg tube mode at Mach number M ∞ = 5 and Reynolds numbers (based on the plate length L = 320 mm) Re ∞L = 23 · 10 6 and 13 · 10 6 . Steady §ow duration is 40 ms. Optical panoramic methods are used for investigation of §ow outside and inside the inlet as well. For this purpose, the cowl and one of two compressing wedges are made of a transparent material. Heat §ux distribution is measured by thin luminescent Temperature Sensitive Paint (TSP). Surface §ow and shear stress visualization is performed by viscous oil containing luminophor particles. The investigation shows that at high contraction ratio of the inlet, an increase of plate or cowl bluntness to some critical value leads to sudden change of the §ow structure.

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Two-dimensional interaction between an incident shock and a turbulent boundary layer in the presence of an entropy layer

Cited by 8 publications

References 19 publications

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

Alterations of Cowl Lip for the Improvement of Supersonic-Intake Performance

Experimental and numerical study of supersonic flow over two blunted wedges

Influence of leading edge bluntness on hypersonic flow in a generic internal-compression inlet

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