Similar Solutions of Compressible Boundary-Layer Equations

Li, Ting-Yi; Nagamatsu, H. T.

doi:10.2514/8.2781

Cited by 26 publications

(15 citation statements)

References 3 publications

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“…In an entirely general discussion of a method of treating the compressible boundary layer equation, Stewartson [9] pointed out in 1949 the existence of "similar" solutions. Stewartson's concept was carried out in great detail by the present authors in 1952 [10]. A new approach to the problem of "similar" solutions was also presented in a recent paper [1 in which it was pointed out that Lees' results in (7) are a special case of the "similar" solutions.…”

Section: Conference On Fl D Mechanicsmentioning

confidence: 84%

“…Eqs 1 and 2 with the boundary conditions of Eqs 6 and 7, in the case of values for m as given in Eq 11, have been integrated on a REAC machine with ' = 1.4 and Y = 1.67 for a range of values of Tw/To. These solutions have previously been reported in [11]. In the present paper, this data will be used to compute, for various Tw/To's, the hypersonic viscous flow characteristics on a flat plate in an air atmosphere or helium atmosphere.…”

Section: Ting-yi LI Ani H T Nagamatsu 277 Hypersonic Viscotaflow Onmentioning

confidence: 90%

“…Recent experimental studies at GALCIT [12] and Princeton [131 have confirmed these conditions. They can be readily utilized to reduce the system of partial differential equations to ordinary equations by the method of [11]. Thus, a theory of hypersonic viscous flow on a noninsulated flat plate can be presented entirely within the framework of the method of "similar" solutions.…”

Section: Conference On Fl D Mechanicsmentioning

confidence: 99%

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Hypersonic Viscous Flow on Noninsulated Flat Plate

Li¹,

Nagamatsu²

1953

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An analytical treatment of the "strong" interaction problem in hypersonic viscous flow on a noninsulated flat plate is presented, using the method of "similar" solutions of the compressible boundary layer equations. Recent experimental data which confirm some of the theoretical results are also discussed. 1 2 yi(w-local heat transfer coefficient Ch.= p.uHG Rex i Po UX free stream Reynolds number on the Rex 9 .0basis of x A,B,C,D defined in Eqs 16-19 .w exponent in the viscosity law Subscripts 'o", I1', wo", aw" refer, respectively, to the stagnation conditions, the conditions at the edge of the boundary layer, the conditions in the free stream, and the conditions on the surface.

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Section: Conference On Fl D Mechanicsmentioning

confidence: 84%

Section: Ting-yi LI Ani H T Nagamatsu 277 Hypersonic Viscotaflow Onmentioning

confidence: 90%

Section: Conference On Fl D Mechanicsmentioning

confidence: 99%

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Hypersonic Viscous Flow on Noninsulated Flat Plate

Li¹,

Nagamatsu²

1953

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“…A limited number of efforts have been made on reacting supersonic flows (see, for example, Buckmaster et al [41], Grosch and Jackson [42], Jackson and Hussaini [43], Im et al [44,45] and Chakraborty et al [46]). For a two-dimensional, laminar, nonreacting boundary layer over a solid body with a pressure gradient, similarity solutions were obtained by Li and Nagamatsu [47], Cohen [48], and Cohen and Reshotko [49] solving the momentum and energy equations transformed by the Illingworth-Stewartson transformation [50][51][52].…”

Section: Reacting Free Mixing Layer In Accelerating Flowsmentioning

confidence: 99%

Turbine Burners: Performance Improvement and Challenge of Flameholding

et al. 2012

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(UCI). He received his Ph.D. degree (1985) from the University of California, Berkeley, with an emphasis in combustion science. He was a Postdoctoral Researcher at Sandia National Laboratories Combustion Research Facility until 1987, when he joined the faculty of Mechanical Engineering at UCI. Dr. Dunn-Rankin's research is primarily in combustion and energy, droplets and sprays, and applications of laser diagnostic techniques to practical engineering systems, with recent emphasis on miniature combustion systems and electrical aspects of flames. He has more than 300 technical publications and presentations in these fields, and he is a Board officer of both the International Combustion Institute and the Institute for the Dynamics of Explosions and Reactive Systems.

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“…See, for example, Buckmaster et al [11], Grosch and Jackson [12], Jackson and Hussaini [13], Im et al [14,15] and Chakraborty et al [16]. For a two-dimensional, laminar, nonreacting boundary layer over a solid body with a pressure gradient, similarity solutions were obtained by Li and Nagamatsu [17], Cohen [18], and Cohen and Reshotko [19] solving the momentum and energy equations transformed by the Illingworth-Stewartson transformation [20][21][22].…”

Section: Reacting Free Mixing Layer In Accelerating Flowsmentioning

confidence: 99%

Turbine-Burner Model: Cavity Flameholding in a Converging, Turning Channel Flow

Colcord¹,

Sirignano²,

Liu³

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A review of turbine-burner research and a discussion of some relevant background issues for this emerging technology are presented. The thermal cycle analysis for augmentative combustion in the passages of the turbine on a turbojet or turbofan engine is discussed, identifying the potential for dramatic improvements in engine performance. The substantial challenges of augmentative combustion integrated with the turbine function are outlined, including the need for flame stabilization in accelerating flows at the 10 5 g levels. Research findings on reacting mixing layers in accelerating flows and flameholding in high-speed flows are reviewed. Descriptions are given of various types of compact combustors which can be used as main combustors or augmentative combustors between turbine stages. An overview is given of recent computational research at UCI on the stabilization of flames in accelerating and turning flows. Two-dimensional computations for Reynolds-averaged turbulent flow through straight and turning channels are discussed. Quasi-two-dimensional representations of reacting, converging (and converging/ turning) channel flows are examined. Two-and three-dimensional computations for time-dependent transitional flows through passages are given for cases with and without cavities. Rossiter modes, found only for the non-reacting cases, are discussed. Various configurations for injection of fuel and air into the cavity are examined. Cavity placements on the inside and outside of the turn are studied to provide different centrifugal accelerations. Some indications for optimizing the cavity design are presented. Effects of the cavity length and depth, injection orientation for fuel and air into the cavity, passage turning radius, and Reynolds number magnitude are discussed. Various hydrodynamic instabilities associated with mixing and combustion in accelerating, turning flows are evaluated, and the needs for future work are identified.

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Similar Solutions of Compressible Boundary-Layer Equations

Cited by 26 publications

References 3 publications

Hypersonic Viscous Flow on Noninsulated Flat Plate

Hypersonic Viscous Flow on Noninsulated Flat Plate

Turbine Burners: Performance Improvement and Challenge of Flameholding

Turbine-Burner Model: Cavity Flameholding in a Converging, Turning Channel Flow

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