Based on recent symmetry-plane boundary-layer solutions, new separation patterns over an inclined body of revolution are presented. Support by experimental evidence as well as differences from other predictions in the literature are noted. Existing three-dimensional separation criteria are mostly inapplicable, and the resulting patterns found are compatible only with MaskelPs general description of separation—i.e., a combination of the free vortex layer type and a bubble type. For a not too blunt body, a bubble type prevails at low incidence, and a free vortex layer type dominates a high incidence. At extremely high incidence or for a more blunt body, a bubble type prevails again.

Separation Patterns of Boundary Layer over an Inclined Body of Revolution

A procedure is suggested for determining the field of application of supersonic separators. The formulation of the problem is given as regards the choice of optimal values of Mach number. The compositions of gas-liquid mixtures are determined as a function of the initial parameters (composition of gas, temperature, pressure, and Mach number). The results are given in the form of temperature, pressure, and Mach number dependences of the composition of the liquid phase of gas-liquid mixture. Primary estimation is made of the efficiency of purification of natural gases depending on their initial parameters.

The procedure for investigation of the efficiency of purification of natural gases in a supersonic separator

A detailed investigation of the laminar boundary-layer flow over a spinning right-circular cone at small angle of attack has shown that there are at least four significant forces contributing to the Magnus force on the cone. In order to calculate these forces, a novel numerical method has been developed which can calculate these small forces over a wide range of flow parameters. The flow conditions have a large influence on the relative magnitude of the Magnus force components, and there can be significant cancelling of the various components.

Magnus Forces on Spinning Supersonic Cones -Part I: The Boundary Layer

The upscale cascade of kinetic energy which characterizes the evolution of turbulent flows that are restricted to two spatial dimensions is mediated by the vortex-pairing interaction In randomly initialized flows on the f -plane, this interaction coarsens the initial vorticity distribution by causing like-signed vortices to amalgamate and thereby leads to the creation of coherent vortical structures of ever-increasing spatial scale In the sequence of analyses discussed herein, we analyse a series of problems of interest from an atmospheric dynamics perspective in which, in spite of their intrinsically three (or 25) dimensionality, the vortex-pairing interaction is nevertheless active and has important phenomenological consequences These problems include the “classical” problems of parallel shear and baroclinic instability as well as the somewhat more exotic problem of vortex dynamics in shallow water flow on the surface of the sphere

The upscale turbulent cascade Shear layers, cyclones and gas giant bands

On the disputes about open separation

: The general problem studied is the propagation of an oblique shock wave through a two-dimensional, steady, non-uniform oncoming flow. A higher order theory is developed to treat the refraction of the incident oblique shock wave by irrotational or rotational disturbances of arbitrary amplitude provided the flow is supersonic behind the shock. A unique feature of the analysis is the formulation of the flow equations on the downstream side of the shock wave. Analytical and numerical solutions to the basic shock refraction relation are presented for a broad range of flows in which the principal interaction occurs with disturbances generated upstream of the shock. These solutions include the passage of a weak oblique shock wave through: a supersonic shear layer, a converging or diverging flow, a pure pressure disturbance, Prandtl-Meyer expansions of the same and opposite family, an isentropic non-simple wave region, and a constant pressure rotational flow. The comparison between analytic and numerical results is very satisfactory. (Author)

The non-linear refraction of shock waves by upstream disturbances in steady supersonic flow

: The general problem studied is the propagation of an oblique shock wave through a two-dimensional steady non-uniform oncoming flow. (Author)

Arnold Goldburg

Papers

The non-linear refraction of shock waves by upstream disturbances in steady supersonic flow

On the non-linear propagation of shock waves through non-uniform incoming flows,