Taylor-Maccoll Hypervelocity Analytical Solutions

Ishimatsu, Takuto; Morishita, Etsuo

doi:10.2322/tjsass.48.46

Cited by 7 publications

(3 citation statements)

References 1 publication

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“…Herein, we employ the same method as in Kerth et al 41,42 to obtain the relevant physical input parameters. Using the HDT freestream properties and the geometry as an input, we assume that the approximation for the Taylor-Macoll solution 50,51 delivers a reasonable estimate for the boundary-layer edge Mach number. We subsequently obtain the boundary-layer edge velocity and then the density through ideal gas relations, which is determined for the denominator of Eq.…”

Section: Experimental Setup a Test Model With Gas Injectionmentioning

confidence: 99%

Displacement of hypersonic boundary layer instability and turbulence through transpiration cooling

Kerth,

Le Page,

Wylie

et al. 2024

Physics of Fluids

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Hypersonic boundary-layer transition onset is commonly characterized in wind tunnel experiments by measuring the surface heat transfer rise above the laminar level. Techniques such as infrared thermography and thin film gauges are routinely used in the field. However, when an interfering cooling effect is present due to foreign gas transpiration, these methods are known to be inadequate. This study uses a 7° half-angle cone at Mach 7 with helium or nitrogen injection through a porous segment within the model frustum. The injector spans 60° in azimuth and is located 300 mm from the sharp nose tip, close to the onset of natural boundary-layer transition. Nitrogen and helium injection reduce the surface heat flux below the laminar level for up to 50 mm downstream of the injector. Comparisons to schlieren images and pressure measurements indicate an advance of transition. Optical diagnostics reveal how instabilities are pushed away from the model surface by the injected gas. This is found through spectral analysis of schlieren images and focused laser differential interferometry signals, which revealed further information about how inaccuracies of detecting transition with surface gauges under the influence of transpiration cooling originate.

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Section: Experimental Setup a Test Model With Gas Injectionmentioning

confidence: 99%

Displacement of hypersonic boundary layer instability and turbulence through transpiration cooling

Kerth,

Le Page,

Wylie

et al. 2024

Physics of Fluids

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“…In the development of the TORNADO's supersonic module [97] it is clearly seen the integration of Mach cone for the delta wing It is the common practice to predict pressure distribution over a cone at high-speed wind channel using Taylor MacColl equation for studying the relation between oblique shock waves and Mach cone which states the normal velocity component on the cone surface becomes small. The Taylor MacColl implementation with hypervelocity calculation by Ishimatsu [98] has the potential to determine the change in velocity of the panels during its transitions from subsonic to supersonic speeds. The method can be implemented for each panel on the wing assuming each panel as a wing in itself going through supersonic flow experiences a shock cone as shown in Fig.…”

Section: Mach-cone Influence In Vlm For Supersonic Configurationsmentioning

confidence: 99%

“…Figure 22. Taylor MacColl equation representing of shock layer and oblique shock relationship for hyper-velocity flow[98].…”

mentioning

confidence: 99%

Review of vortex lattice method for supersonic aircraft design

Joshi

Thomas

2023

Aeronaut. j.

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There has been a renewed interest in developing environmentally friendly, economically viable, and technologically feasible supersonic transport aircraft and reduced order modeling methods can play an important contribution in accelerating the design process of these future aircraft. This paper reviews the use of the vortex lattice method (VLM) in modeling the general aerodynamics of subsonic and supersonic aircraft. The historical overview of the vortex lattice method is reviewed which indicates the use of this method for over a century for development and advancements in the aerodynamic analysis of subsonic and supersonic aircraft. The preference of VLM over other potential flow-solvers is because of its low order highly efficient computational analysis which is quick and efficient. Developments in VLM covering steady, unsteady state, linear and non-linear aerodynamic characteristics for different wing planform for the purpose of several different types of design optimisation is reviewed. For over a decade classical vortex lattice method has been used for multi-objective optimisation studies for commercial aircraft and unmanned aerial vehicle’s aerodynamic performance optimisation. VLM was one of the major potential flow solvers for studying the aerodynamic and aeroelastic characteristics of many wings and aircraft for NASA’s supersonic transport mission (SST). VLM is a preferred means for solving large numbers of computational design parameters in less time, more efficiently, and cheaper when compared to conventional CFD analysis which lends itself more to detailed study and solving the more challenging configuration and aerodynamic features of civil supersonic transport.

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Closed-form approximation for supersonic flow over a cone

Forbes

Hindle

2018

Shock Waves

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Taylor-Maccoll Hypervelocity Analytical Solutions

Cited by 7 publications

References 1 publication

Displacement of hypersonic boundary layer instability and turbulence through transpiration cooling

Displacement of hypersonic boundary layer instability and turbulence through transpiration cooling

Review of vortex lattice method for supersonic aircraft design

Closed-form approximation for supersonic flow over a cone

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