Expressions for predicting 3-D shock wave-turbulent boundary layer interaction pressures and heating rates

Scuderi, Lee

doi:10.2514/6.1978-162

Cited by 17 publications

(4 citation statements)

References 3 publications

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“…Scuderi, 3 Hayes, 12 and others proposed analytical methods for estimating pressure and heating rate distribution for planar three-dimensional interaction flow regions. These analytical methods are based on observations of experimental results and correlations of empirical data from many sources.…”

Section: Results and Comparisonsmentioning

confidence: 99%

High-speed Interference Heating Loads and Pressure Resulting from Elevon Deflections

Johnson

Kaufman

1980

Journal of Aircraft

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Effects of elevon-induced three-dimensional shock wave turbulent boundary-layer interactions on hypersonic aircraft surfaces are analyzed. Detailed surface pressure and heating rate distributions obtained on wing-elevonfuselage models representative of aft portions of hypersonic aircraft are compared with analytical and experimental results from other sources. Examples are presented that may be used to evaluate the adequacy of current theoretical methods for estimating the effects of three-dimensional shock wave turbulent boundary-layer interactions on hypersonic aircraft surfaces. Nomenclature H = ratio of disturbed to undisturbed heat transfer coefficients at same location h = heat transfer coefficient, Wlm 2 K M = Mach number P = pressure ratio, (P/P^) disturbed/CP/P^) undisturbed p = pressure, Pa R c = Reynolds number based on freestream flow conditions and length (64.14 cm wing root chord) / =time, s T = temperature, K x -streamwise distance measured along surface of wing and elevon from wing apex (wing leading edge for unswept wing), cm y = spanwise distance measured outboard from inboard edge of the elevon, cm z = distance measured on end plate surface upward from wing surface, cm e = elevon deflection angle, deg 0 = elevon shock wave angle, deg A = wing sweepback angle, deg Subscripts aw = adiabatic wall / = initial inv = value calculated inviscidly, neglecting separation pc = phase change of paint coating PK = peak (maximum conditions) / = stagnation conditions of freestream tunnel flow 1 = local flow conditions over wing and over wing and end plate surfaces oo = freestream flow conditions

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Section: Results and Comparisonsmentioning

confidence: 99%

High-speed Interference Heating Loads and Pressure Resulting from Elevon Deflections

Johnson

Kaufman

1980

Journal of Aircraft

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“…Data for surface streamline locations, surface pressure, heat transfer and skin friction is available [105] [106]. Rodi and Dolling present a study of heat transfer comparing three empirical correlations for the peak heat transfer from Lee and Settles [66], Scuderi [103], and [45], with very good agreement with the experimental data for the normal Mach number range from 1.3 to 2.2 approx. The peak pressure correlation from Scuderi [103] is also compared with experimental data in [66], again obtaining satisfactory agreement.…”

Section: Free Stream Shockmentioning

confidence: 89%

Numerical and experimental investigation of hypersonic streamwise vortices and their effect on mixing

Gomez¹,

Ramón²

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Scramjet propulsion is a promising technology that could lead to substantial improvements in cost and flexibility for access to space for satellite placement into Low Earth Orbit. However, scramjet development is hindered by different technological issues. Amongst these, fast and efficient fuel-air mixing, and heat management, are key areas. By increasing mixing rate, the combustor can be shortened while keeping a high combustion efficiency. This reduces drag and heat losses, highly improving the feasibility and viability of scramjet engine designs. Several techniques have been proposed to increase mixing rate in scramjets, such as hypermixers and strut injectors. However, these techniques improve mixing at the expense of increased losses and local heat loads.For this reason, the use of naturally occurring vortices in scramjet flowfields for mixing enhancement came into consideration. Most scramjet geometries inherently generate streamwise vortices. Therefore, there are no increased losses when using these vortices for mixing enhancement. However, these vortices are weaker than those generated by hypermixers or struts.Hence, the ability of these vortices to effectively enhance mixing rate has to be evaluated.This work addresses the study of the interaction between streamwise vortices in scramjet flowfields and fuel injected through an inclined porthole injector to establish optimum arrangements for scramjet performance. The analysis of this interaction is performed numerically and experimentally. Numerical RANS simulations are used as the principal tool to analyse and describe the vortex-injection interaction. In addition, experimental data was gathered to assess the validity of the numerical approach. Scramjet flows are highly complex. To study the effect of the vortex in isolation, a simplified, canonical geometry, consisting of a flat plate with a normal fin is used. The swept shock generated by the fin interacts with the flat plate boundary layer, inducing the formation of a vortex. The features of this vortex are equivalent to those of vortices present in real scramjet flowfields. Moreover, this geometry allows to control the vortex intensity by modifying the fin compression angle. The flat plate incorporates a porthole injector, from which Hydrogen fuel is injected into the vortex. The interaction between the injected fuel and the streamwise vortex was studied focusing on its effect on mixing. Moreover, its effects on maximum wall heat flux, and fuel combustion were also analysed.

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“…It is also observed that, for complex geometries like intake or control surfaces, the transition may occur in the region of adverse pressure gradients due to SBLIs. According to Scuderi (1978), unlike the attached flow where the pressure and the heat transfer rate increase gradually, in a separated flow, the rise in peak pressure and the heat transfer rate is separated by a plateau region [51]. Dolling (2001) mentioned that two main aspects of an SBLI induced aero-thermal heating are the location of its occurrence and the magnitude of the thermal load [52].…”

Section: High Thermal Loadsmentioning

confidence: 99%

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

Jana

Kaushik

2022

Adv. Aerodyn.

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The primary focus of the present survey is to categorize the results of various investigations on the Shock/Boundary-Layer Interactions (SBLIs), their repercussions, and the effective ways to control them. The interactions of shock waves with the boundary layer are an important area of research due to their ubiquity in several applications ranging from transonic to hypersonic flows. Therefore, there is a need for a detailed inspection to understand the phenomena to predict its characteristics with certain accuracy. Considering this in mind, this article presents some key features of the physical nature of SBLIs, their consequences, and the control techniques in a sequential manner; in particular, the passive control techniques for the supersonic and hypersonic intakes are reviewed in detail.

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Expressions for predicting 3-D shock wave-turbulent boundary layer interaction pressures and heating rates

Cited by 17 publications

References 3 publications

High-speed Interference Heating Loads and Pressure Resulting from Elevon Deflections

High-speed Interference Heating Loads and Pressure Resulting from Elevon Deflections

Numerical and experimental investigation of hypersonic streamwise vortices and their effect on mixing

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

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