Supersonic scattering of a wing-induced incident shock by a slender body of revolution

Федоров, А. В.; Malmuth, N.; Soudakov, Vitaly

doi:10.1017/s0022112007006714

Cited by 10 publications

(12 citation statements)

References 9 publications

(10 reference statements)

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“…The theoretical results agree well with corresponding numerical solutions of three-dimensional Euler equations and with experiment [6]. For example, the difference between the experimental lift distribution (measured on the bluntbase parabolic body of revolution in the flowfield induced by a circular-arc wing in the Mach 2 freestream) and the theoretical one is less than 10%, despite the fact that the body radius varies in the interaction region and the wing thickness is not very small [15].…”

supporting

confidence: 80%

“…As shown in [15], the second and higher scatterings also give zero contributions in the total lift. However, this limit is achieved for quite largex.…”

Section: A Theoretical Analysismentioning

confidence: 79%

“…(10). As shown in [15], the local lift coefficient induced by a plane wave of amplitude B 1 is c L 8i…”

Section: A Theoretical Analysismentioning

confidence: 95%

“…Detailed theoretical analysis of multiple shock-wave scatterings for the wedge-slenderbody configuration was conducted in [15]. The problem was analyzed using the slender-body theory with the ratio of the body radius to the separation distance being treated as a small parameter.…”

mentioning

confidence: 99%

“…The problem is analyzed using two essentially different approaches. The first is based on the shock wave scattering theory and provides a local solution, which is an extension of the theoretical model [15] to the case of two-body interaction (Sec. II).…”

mentioning

confidence: 99%

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Theoretical Modeling of Two-Body Interaction in Supersonic Flow

2010

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Atmospheric and space launch stage separation depends on the aerodynamic interference between separating bodies. Quick means of estimating and controlling repulsion or attraction lift associated with this interaction are an important enabling technology to achieve the best compromise between launch separation rocket motor weight and safe staging. Asymptotic methods, scattering, and slender-body theories are used to obtain systematic approximation schemes that advantageously couple with computational methods. Theoretical solutions for the lift interference between two bodies in supersonic flow agree well with numerical solutions. The theory sheds light on important scattering phenomena not previously recognized as relevant to this problem. The analysis helps to identify lumped dimensionless parameters and provides scaling laws as well as closed-form expressions for the interference not accessible solely from computations. These results can be used for interpolation and extrapolation of computational fluid dynamics solutions as well as efficient testing and design of flight vehicles. Nomenclature A = cross-sectional body area a = body radius C L = integral lift coefficient c L = local lift coefficient h = vertical distance between bodies' axes L = lift force l = body length l n = body nose length M = Mach number p = pressure T = temperature u, v, w = velocity components x, y, z = Cartesian coordinates x 0 = streamwise distance from the nose tip to the point where shock crosses the body axis = induced angle of attack "= characteristic flow deflection = density = perturbation potential

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supporting

confidence: 80%

“…As shown in [15], the second and higher scatterings also give zero contributions in the total lift. However, this limit is achieved for quite largex.…”

Section: A Theoretical Analysismentioning

confidence: 79%

“…(10). As shown in [15], the local lift coefficient induced by a plane wave of amplitude B 1 is c L 8i…”

Section: A Theoretical Analysismentioning

confidence: 95%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Theoretical Modeling of Two-Body Interaction in Supersonic Flow

2010

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Aerodynamic interference between high-speed slender bodies

2010

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Significant aerodynamic interference can occur between high-speed bodies in close proximity. A complex flowfield develops where shock and expansion waves from a generator body impinge upon the adjacent receiver body. The pressure and flow angularity changes which occur across these disturbances modify the body aerodynamics. The aim of this research is to quantify the aerodynamic interference effects for multi-body configurations and understand the relevant flow physics.The interference aerodynamics for slender bodies in a supersonic flow were investigated through a parametric wind tunnel study. The receiver bodies were finned and un-finned configurations. The effect of lateral and axial body separations, receiver incidence and the strength of the disturbance field were investigated. Measurements included forces and moments, surface pressures and flow visualisations. Supporting computations using steady-state, viscous predictions provided a deeper understanding of the underlying aerodynamics and flow mechanisms. Good agreement was found Many people have contributed to the completion of this research. I would like to take time to thank them. My supervisor David MacManus for his guidance and help throughout. I would especially like to thank him for the many occasions when he took my work home with him to read and provide feedback during the writing process. I would like to acknowledge the financial support of the UK MOD. The investigation which is the subject of this report was initiated by the Air Systems Department Dstl and was carried out under the terms of Contract No RD025 -1962. Additional funding was also provided through an ESPRC CASE award. I would also like to thank Dstl for the release of experimental data which greatly enhanced this research. Trevor Birch for his constant support and guidance throughout. In particular, I would like to thank him for making arrangements for me to undertake two placements at Dstl. These aided my research and I enjoyed my time at Dstl immensely. Moreover, I would like to also thank Ben Shoesmith and Kristian Petterson who gave up alot of their own time in order to assist me. Their help with IMPNS and Cobalt was particularly useful.

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