Viscous Effects and Truncation Effects in Axisymmetric Busemann SCRamjet Intakes

Flock, Andreas K.; Guelhan, Ali

doi:10.2514/6.2015-0108

Cited by 4 publications

(6 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…To accommodate for viscous effects, we used a viscous correction 6,9,10 ; therefore, we calculated various boundary layer properties, such as displacement thickness or skin friction along the Busemann intake contour for the inviscid pressure distribution. With the displacement thickness we widened the Busemann geometry to accommodate for the additional contraction by the boundary layer and with the skin friction, we calculated the viscous forces along the intake wall.…”

Section: A Intake Modulementioning

confidence: 99%

See 1 more Smart Citation

Axisymmetric SCRamjet Engine Design and Performance Analysis

Flock¹,

Riehmer²,

Guelhan³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

Self Cite

View full text Add to dashboard Cite

In the present work, we treat the SCRamjet engine as a system, by coupling different analytical design tools. For the intake portion a Busemann tool was used, the combustion chamber was modeled with a onedimensional reactor, and the nozzle was modeled with the method of characteristics. Performance parameter are discussed while we mainly focus on specific impulse. We used numerical simulations to validate the modeling of the combustion chamber and it turned out that after analytically forcing ignition, the numerical results matched the predictions best. Furthermore, we validated the analytical approach with numerical results and obtained good agreement. According to the analytical tool, for a constant intake pressure ratio of 80 the engine did not ignite at Mach numbers lower than 6 and the specific impulse dropped from 3500 s at Mach 6 to 1200 s and 500 s for Mach 8 and 10, respectively. Due to the small geometry and therefore high friction drag, specific impulse became negative at Mach 11.

show abstract

Section: A Intake Modulementioning

confidence: 99%

“…In the present paper, we treat the SCRamjet engine as a system, while bringing together several tools and experiences gained in previous studies 5,6 . A schematic overview of the different tool-modules as well as of the input or boundary conditions, which need to be fed into the tool, is provided in figure 1.…”

Section: Introductionmentioning

confidence: 99%

Axisymmetric SCRamjet Engine Design and Performance Analysis

Flock¹,

Riehmer²,

Guelhan³

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

Self Cite

View full text Add to dashboard Cite

show abstract

“…Как правило, пограничный слой формируется на передней кромке и растет под влиянием свойств передней кромки и ламинарно-турбулентного перехода. Однако из-за эффекта вытеснения пограничного слоя область сжатия изменяется, и изменяются ее свойства (геометрия) [14]. Это влияет на развитие течения в ядре потока и на развитие пограничного слоя.…”

Section: Introductionunclassified

Flow Realization in Hypersonic Air Inlet with Spatial Compression

Goldfeld¹,

Starov²

2019

SJPhys

View full text Add to dashboard Cite

“…The air intake of the scramjet plays a key role in scramjet operation by compressing the inflow to high pressure and temperature for combustion, while ensuring a high total pressure for thrust production. The theoretical axisymmetric Busemann intake is generally regarded as producing an efficient compression field and is often used as a basis for hypersonic intake studies [2,[7][8][9][10]13]. The axisymmetric full Busemann intake for a Mach 8 freestream can achieve a total pressure recovery of 97% and uniform outflow in inviscid flow, with the 3% loss occurring over a downstream conical shock wave at the end of the initial isentropic compression [8].…”

Section: Introductionmentioning

confidence: 99%

Viscous Correction and Shock Reflection in Stunted Busemann Intakes

Ogawa

Shoesmith

Mölder

et al. 2018

Shock Wave Interactions

View full text Add to dashboard Cite

Air intakes play a crucial role in hypersonic air-breathing propulsion by compressing incoming airflow to high pressure and temperature for combustion. Axisymmetric Busemann intakes can achieve highly efficient compression for scramjet engines in inviscid flow. In practice, however, viscous effects exert significant influence on the flowfield and performance of scramjet intakes, necessitating effective methods for viscous correction and intake shortening. The present study develops a robust correction methodology by coupling viscous flow simulations with a wall correction method based on local displacement thickness of the boundary layer, whose edge is detected based on the total enthalpy profile. This iterative correction process is applied to hypersonic stunted Busemann intakes and supersonic M-flow ring geometries. Flow features in the initial inviscid fields are successfully reproduced in the presence of viscosity for both applications, except for highly stunted Busemann intakes, where the mode transition to Mach reflection occurs at different shortening lengths.

show abstract

Viscous Effects and Truncation Effects in Axisymmetric Busemann SCRamjet Intakes

Cited by 4 publications

References 19 publications

Axisymmetric SCRamjet Engine Design and Performance Analysis

Axisymmetric SCRamjet Engine Design and Performance Analysis

Flow Realization in Hypersonic Air Inlet with Spatial Compression

Viscous Correction and Shock Reflection in Stunted Busemann Intakes

Contact Info

Product

Resources

About