Use of flows with straight sonic line in nozzles with corners

�. G. Shifrin

doi:10.1007/bf01094828

Computational Analysis of the Transonic Flow Field of Two-Dimensional Minimum Length Nozzles

Journal of Fluids Engineering ◽

10.1115/1.2909521 ◽

1991 ◽

Vol 113 (3) ◽

pp. 479-488 ◽

Cited By ~ 11

Author(s):

B. M. Argrow ◽

G. Emanuel

Keyword(s):

Supersonic Flow ◽

Flow Field ◽

Method Of Characteristics ◽

Reynolds Numbers ◽

Boundary Layer Separation ◽

Minimum Length ◽

Two Dimensional ◽

Sonic Line ◽

Inlet Geometry ◽

Straight Sonic Line

The method of characteristics is used to generate supersonic wall contours for two-dimensional, straight sonic line (SSL) and curved sonic line (CSL) minimum length nozzles for exit Mach numbers of two, four and six. These contours are combined with subsonic inlets to determine the influence of the inlet geometry on the sonic-line shape, its location, and on the supersonic flow field. A modified version of the VNAP2 code is used to compute the inviscid and laminar flow fields for Reynolds numbers of 1,170, 11,700, and 23,400. Supersonic flow field phenomena, including boundary-layer separation and oblique shock waves, are observed to be a result of the inlet geometry. The sonic-line assumptions made for the SSL prove to be superior to those of the CSL.

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Plane-Parallel and Axisymmetric Flows with a Straight Sonic Line

Computational Mathematics and Mathematical Physics ◽

10.1134/s0965542519040079 ◽

2019 ◽

Vol 59 (4) ◽

pp. 610-629

Author(s):

A. N. Kraiko ◽

N. I. Tillyayeva ◽

T. V. Shamardina

Keyword(s):

Sonic Line ◽

Plane Parallel ◽

Straight Sonic Line

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Comparison of Minimum Length Nozzles

Journal of Fluids Engineering ◽

10.1115/1.3243546 ◽

1988 ◽

Vol 110 (3) ◽

pp. 283-288 ◽

Cited By ~ 26

Author(s):

B. M. Argrow ◽

G. Emanuel

Keyword(s):

Inflection Point ◽

Method Of Characteristics ◽

Accurate Method ◽

The Other ◽

Minimum Length ◽

Turn Angle ◽

Sonic Line ◽

The One ◽

Axisymmetric Minimum Length Nozzle ◽

Straight Sonic Line

A second-order accurate method-of-characteristics algorithm is used to determine the flow field and wall contour for a supersonic, axisymmetric, minimum length nozzle with a straight sonic line. Results are presented for this nozzle and compared with three other minimum length nozzle configurations. It is shown that the one investigated actually possesses the shortest length as well as the smallest initial wall turn angle at the throat. It also has an inflection point on the wall contour, in contrast to the other configurations.

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The Sonic Line of a Propagating Detonation Wave

AIAA Scitech 2020 Forum ◽

10.2514/6.2020-0444 ◽

2020 ◽

Author(s):

Hardeo M. Chin ◽

Jessica Chambers ◽

Jonathan Sosa ◽

Kareem A. Ahmed ◽

Alexei Poludnenko ◽

...

Keyword(s):

Detonation Wave ◽

Sonic Line

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Focusing effects in two-dimensional, supersonic flow

Philosophical Transactions of the Royal Society of London. Series A, Mathematical and Physical Sciences ◽

10.1098/rsta.1949.0008 ◽

1949 ◽

Vol 242 (844) ◽

pp. 153-171 ◽

Cited By ~ 14

Keyword(s):

Method Of Characteristics ◽

Inverse Transformation ◽

Two Dimensional ◽

Perfect Gas ◽

Geometrical Method ◽

Independent Variables ◽

Flow Problems ◽

Sonic Line ◽

Hodograph Transformation ◽

Line Patterns

The steady, supersonic, irrotational, isentropic, two-dimensional, shock-free flow of a perfect gas is investigated by a new, geometrical, method based on the use of characteristic co-ordinates. Some of the results apply also to more general problems of compressible flow involving two independent variables (§1). The method is applied in particular to the treatment of the non-linear, non-analytic features. The variation in magnitude of discontinuities of the velocity gradient is determined as a function of the Mach number in § 4. The reflexion at the sonic line of such discontinuities is treated in § 7. The isingularities of the field of flow are discussed in §§ 5 to 5.4; Craggs’s (1948) results are extended to the case when the velocity components are not analytic functions of position, and to the case in which both the hodograph transformation and the inverse transformation are singular.. Examples are given of singularities that occur in familiar flow problems, but have not hitherto been described (§§ 5.3, 5.4). Some properties are established of the geometry in the large of Mach line patterns; these properties are useful for the prediction of limit lines (§ 5.2). The problem of the start of an oblique shockwave in the middle of the flow is briefly reviewed in §6. In the appendix it is shown that the conventional method of characteristics for the numerical treat ment of two-dimensional, isentropic, irrotational, steady, supersonic flows must be modified near a branch line if a loss of accuracy is to be avoided.

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