Turbulent Boundary Layer in Compressible Fluids

Driest, E. R. Van

doi:10.2514/2.7048

Cited by 107 publications

(59 citation statements)

References 3 publications

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“…Figure 14 shows a semi-logarithmic representation of the latter turbulent profile (x = 100 mm) in terms of the inner variables y + = yu τ /ν w and u + = u eq /u τ . Here u τ = 19.6 m/s presents the friction velocity, ν w is the kinematic viscosity evaluated at the wall, and u eq is the Van Driest effective velocity (Van Driest 1951). The log region can be clearly distinguished in the PIV data, and also the start of the viscous sublayer is resolved.…”

Section: Particle Image Velocimetrymentioning

confidence: 90%

High-resolution PIV measurements of a transitional shock wave–boundary layer interaction

2015

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Section: Particle Image Velocimetrymentioning

confidence: 90%

High-resolution PIV measurements of a transitional shock wave–boundary layer interaction

2015

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“…These correlations are the minor functions of dimension and time coordinates. Should the conventional averaging time procedure be substituted by the density weighted mean, used in the work [3] and developed in [4] and [5], the density average velocity rate o i U results from the defining relation:…”

Section: The Rules Of Averaging With the Observance Of Density Changesmentioning

confidence: 99%

The convection term evaluation of the turbulence kinetic energy balance in a flame with medium density changes

Grodzki

2012

Sci. Res. Inst. Math. Comp. Sci.

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Abstract. This paper consists of an analysis pertaining to the turbulence kinetic energy balance equation with the acknowledgement of burning medium density change influence. The evaluation of the convection element value and of the density change influence on the turbulence kinetic energy balance has been attempted. Experimental data obtained by means of laser Doppler anemometry and the radial distributions of average temperatures of a burning jet have been exploited in the present paper.

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“…For RLV-TD, heating rates at the stagnation point of nose cap for ascent and descent phases of the flight were estimated using Fay and Riddell correlation 1 . For locations other than the stagnation point, heat flux was computed based on Van Driest theory for laminar and turbulent flow 2,3 . Beckwith and Gallagher 4 correlation was used for the wing and vertical tail stagnation by assuming an infinite swept cylinder for the flows with an angle of incidence.…”

Section: Heat Flux Estimationmentioning

confidence: 99%

Aerothermal Design, Qualification and Flight Performance

2018

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Reusable Launch Vehicle-Technology Demonstrator (RLV-TD) experiences severe thermal environment during its ascent as well as re-entry into the atmospheric regime. Structures should be designed to withstand this thermal load. Thermal environments were estimated for RLV-TD and depending on the peak heat flux and heat load, hot structure design for nose cap, wing, vertical tail and control surfaces was developed. Thermal protection system (TPS) using silica tile and flexible insulation was designed to protect the windward and leeward regions respectively. It is essential to verify and establish the design and also physically corroborate the actual thermal performance. Besides the design, the hot structures and TPS functionality as a system has to be qualified and thereby yield full confidence on the total performance during flight. To qualify the hot structures and TPS, various qualification tests were undertaken. The demonstration of their fly-ability and qualification under the combined effect of structural and thermal load was carried out successfully for all structures. This article provides details of aerothermal design of RLV-TD and various qualification tests carried out. Comparison of the estimated structure temperatures with measured temperatures in flight shows the robustness of the design methodologies adopted.

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Turbulent Boundary Layer in Compressible Fluids

Cited by 107 publications

References 3 publications

High-resolution PIV measurements of a transitional shock wave–boundary layer interaction

High-resolution PIV measurements of a transitional shock wave–boundary layer interaction

The convection term evaluation of the turbulence kinetic energy balance in a flame with medium density changes

Aerothermal Design, Qualification and Flight Performance

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