Flow Properties of a Supersonic Turbulent Boundary Layer with Wall Roughness

Latin, Robert M.; Bowersox, Rodney D. W.

doi:10.2514/2.862

Cited by 49 publications

(8 citation statements)

References 14 publications

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“…An aerodynamically smooth plate and fully rough regularly spaced surface roughness pattern with k, values similar to those used in Latin and Bowersox (2000).…”

Section: Roughnessmentioning

confidence: 99%

“…Numerous experiments on zero pressure gradient surface roughness flows have been performed on both low speed [Nikuradse (1933), Corrsin and Kistler (1955), Perry et al (1969), Simpson (1973), Antonia and Wood (1975), and Schlichting (2003)], and high speed flows [Goddard (1959) and Berg (1979), Fan and Bowersox (1999), Latin and Bowersox (2000), and Pritchett and Bowersox (2001)]. In summary for fully rough boundary layer flows the basic trends show an increase of the turbulence intensities by as much as 30 -40% and an increase skin friction by as much as a factor of 2, clearly representing an increase in the turbulent production mechanisms and an alteration of the turbulent dissipation.…”

Section: Introductionmentioning

confidence: 99%

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Influence of Surface Roughness on the Second Order Transport of Turbulence in Non-Equilibrium Boundary Layers

Sharif¹,

Bowersox²

2006

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“…An aerodynamically smooth plate and fully rough regularly spaced surface roughness pattern with k, values similar to those used in Latin and Bowersox (2000).…”

Section: Roughnessmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Influence of Surface Roughness on the Second Order Transport of Turbulence in Non-Equilibrium Boundary Layers

Sharif¹,

Bowersox²

2006

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“…Latin and Bowersox [13] experimentally measured and characterized the effects of a number of rough-walled topologies including equivalent sand-grain roughness and distributed machined roughness on the mean and turbulent flow quantities of a Mach 2.9 supersonic TBL. It was found that smaller roughness elements relative to the boundary layer thickness increased skin friction losses.…”

Section: Introductionmentioning

confidence: 99%

The Impact of Streamwise Steps and Cavities Geometry on Supersonic Turbulent Boundary Layer

Ch’ng

Teryaev

Sidhu

et al. 2020

CFDL

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In some cases, the nozzle of a rocket engine could deform during manufacturing or testing, flare up and distort during operation in such a way that periodically repeating structures of depressions and protrusions form on the wall surface. Complex configurations of roughness topologies have been experimentally observed to form due to this fluid-structure interaction and have been known to distort the boundary layer and increase local drag and heat transfer. A numerical experiment was carried out using ANSYS FLUENT to assess the effects of geometry (streamwise wavelengths ? and length-to-depth ratios (L/D)) of discrete roughness topologies in the form of steps and cavities on flow field distortions and resulting total drag. It was found that cavity L/D ratios of 19.8 – 23.1 and 12.8 – 15.5 yielded the highest drag coefficients. The flow fields over these periodic arrays exhibited closed and a combination of closed cavity type features, and it can be concluded that the flow phenomena associated with separation caused by forward facing steps in closed cavity type topologies contributed the most to the total drag. L/D ratios of 6.3 – 8.4 exhibited the lowest drag coefficient. The lower drag coefficient is due to the modification of the turbulent boundary layer by the trapped coherent vortical structure within the cavities. Pressure forces become more dominant as the surface wavelength is decreased. For all cases, there was a pronounced increase in the boundary layer thickness after each successive cavity.

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“…Second, fundamental information is to be acquired with the goal of providing improved understanding of the flow physics, which will ultimately lead to improved prediction methods. As an example, the data generated in the AFOSR Grant F49620-98-1-0038, as reported in Latin and Bowersox (2000), were used to validate current numerical methods being used to design the hypersonic nozzle for the Air Force AEDC RDHWT/MARIAH II project. Tables TABLE 1 FREESTREAM FLOW CONDITIONS 19 TABLE 2 Access-to-space vehicle development (also listed in the AFOSR BAA) will also benefit from this research.…”

Section: Sponsoring / Monitoring Agency Name(s) and Address(es)mentioning

confidence: 99%

“…Second, fundamental information is planned with the goal of improved understanding of the flow physics, which will ultimately lead to improved prediction methods. As an example, the data generated in AFOSR Grant F49620-98-1-0038, as reported in Latin and Bowersox (2000) were used to validate numerical methods that are currently being used to design the hypersonic nozzle for the Air Force AEDC RDHWT/MARIAH II project.…”

Section: Technology Transitionsmentioning

confidence: 99%

Influence of Surface Roughness and Freestream Turbulence on the Second Order Transport of Turbulence in Non-Equilibrium Boundary Layers

Bowersox¹

2002

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Flow Properties of a Supersonic Turbulent Boundary Layer with Wall Roughness

Cited by 49 publications

References 14 publications

Influence of Surface Roughness on the Second Order Transport of Turbulence in Non-Equilibrium Boundary Layers

Influence of Surface Roughness on the Second Order Transport of Turbulence in Non-Equilibrium Boundary Layers

The Impact of Streamwise Steps and Cavities Geometry on Supersonic Turbulent Boundary Layer

Influence of Surface Roughness and Freestream Turbulence on the Second Order Transport of Turbulence in Non-Equilibrium Boundary Layers

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