2 edition of **Calculation of two-dimensional inlet flow fields in a supersonic free stream** found in the catalog.

Calculation of two-dimensional inlet flow fields in a supersonic free stream

Sedat Biringen

- 379 Want to read
- 1 Currently reading

Published
**1980**
by National Aeronautics and Space Administration, Scientific and Technical Information Office, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
.

Written in

- Aerodynamics.

**Edition Notes**

Statement | S.H. Biringen and O.J. McMillan ; prepared for Langley Research Center under contract NAS1-15305. |

Series | NASA contractor report -- NASA CR-3221. |

Contributions | McMillan, Oden J., United States. National Aeronautics and Space Administration. Scientific and Technical Information Office., Langley Research Center. |

The Physical Object | |
---|---|

Pagination | iii, 162 p. : |

Number of Pages | 162 |

ID Numbers | |

Open Library | OL17545109M |

Types of two-dimensional flows Uniform source flow. A radially symmetrical flow field directed outwards from a common point is called a source flow. The central common point is the line source described above. Fluid is supplied at a constant rate from the source. As the fluid flows outward, the area of flow increases. The inflow and INJ region are the inlet of the flow fields and the fluidic oscillator, respectively. The flow conditions of Inflow and injected fuel are given in Table 1. Extrapolation conditions were applied as the boundary conditions of the outflow to simulate the Author: Eun Cheol Lee, Seung-Won Cha, Hee-Soo Kwon, Tae-Seong Roh, Hyoung Jin Lee.

A two-dimensional steady irrotational flow of a perfect fluid can be de-scribed either by its potential (in the following denoted by p) or by the stream function, p. In the case of an incompressible fluid p and p are connected by the Cauchy-Riemann equations, so that p+ip is an analytic function,/, of a complex variable. Finally, the leading edge of the inlet is deﬁned by the initial intersection of the calculated stream traces and the primary oblique shock. In a traditional two-dimensional rectangular inlet, compression is induced primarily by the upper and/or lower inlet surfaces. These surfaces are nominally planar and in turn create planar shocks.

A theory for base pressures in transonic and supersonic flow / (Urbana, Ill.: Mechanical Engineering Dept., Univ. of Illinois, May ), by Helmut Hans Korst, M. E. Childs, R. H. Page, and University of Illinois (Urbana-Champaign campus). Engineering Experiment Station (page images at HathiTrust; US access only). The nozzle wall profile obtained by this calculation for a design Mach number of is shown below. Figure.4 Mach contour nozzle So far, only the supersonic section of the nozzle has been designed. The subsonic, convergent section is chosen arbitrarily by joining the nozzle throat to the inlet (65mm) by a smooth Size: KB.

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Get this from a library. Calculation of two-dimensional inlet flow fields in a supersonic free stream: program documentation and test cases. [Sedat Biringen; Oden J McMillan; United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.; Langley Research Center.].

Calculation of Two-Dimensional Inlet Flow Fields in a Supersonic Free Stream - Program Documentation and Test Cases S. Biringen and 0. McMillan Nielsen Engineering G Research, Inc. M ouutain View, Ca Ziforrzia Prepared for Langley Research Center under Contract NASl National Aeronautics.

3) Inlet Geometry Model • The Inlet Geometry Model describes and parameterizes the shape of the various inlets of interest for the Inlet Tools.

• A set of Basic Inlet Shapes defines the scope of possible geometries. • The inlet flow field is divided into Parts that further helps establish parameters for defining the geometry. A Numerical Analysis on Three-Dimensional Flow Field in a Supersonic Bump Inlet Article in Journal of Mechanical Science and Technology 21(2) January with 34 Reads.

Abstract. The method of characteristics is a workable numerical method for the calculation of unsteady two-dimensional inviscid flow at subsonic, transonic, and supersonic speeds, and for the generation of steady flow gh the basic scheme is quite well developed, more work needs to be done, particularly in the case of subsonic free : Chong-Wei Chu, Stefan Nadir.

A two-dimensional inlet of external compression with the increased flow rate factor at high supersonic velocities is constructed by the method of gasdynamic design.

Its feature is that a flow with the initial oblique shock wave and the subsequent centered isentropic compression wave is formed over the external compression ramp of the by: 7.

Thomas B. Gatski, Jean-Paul Bonnet, in Compressibility, Turbulence and High Speed Flow (Second Edition), Flows with Shocks. In supersonic flows, the presence of shocks is hardly avoidable and flow control is often the only solution to minimize penalties associated with drag, vibrations, noise, obvious example is in supersonic flight of supersonic civil or.

inlet that is accurate to within 10% but requires less than a few seconds of computational time. To achieve this goal, a reduced-order model is presented, which predicts the solution of a steady two-dimensional supersonic ﬂow through an inlet or around any other two-dimensional geometry.

The model assumes that the ﬂow is supersonic. The supersonic mixing layer flow, consisting of a relatively cold, slow diluted hydrogen stream and a hot, faster air stream, is numerically simulated with detailed transport properties and. The cross section of a typical subsonic inlet and its geometric parameters are shown in Fig.

The inlet area A 1 is based on the flow cross section at the inlet highlight. Because the subsonic inlet can draw in airflow whose free stream area A 0 is larger than the inlet area A 1, variable inlet geometry is not.

Section 6: Gutter and Inlet Equations Anchor: #i Gutter Flow. The ponded width is a geometric function of the depth of the water (y) in the curb and gutter section. The spread is usually referred to as ponded width (T), as shown in Figure 10. of supersonic inlet two-dimensionally. Loth et al.

[8] utilized a meso ap ow control for a ramped inlet at a free stream Mach number of 2. They further tested this method of ow control for the same inlet equipped with a bleed system and compared both results with the solid surface (no-control) con guration.

In addition. The 2-D internal steady flow of the scramjet inlet-isolator was numerically simulated by the CFD method. The static pressure contours of the scramjet inlet-isolator under different boundary thickness and different back pressure were given. The numerical simulation results of two kinds of reasons which make the inlet un-start are obtained.

One is the boundary layer thickness and Author: Da Min Cao, Hong Yang Lv, Xing Yuan Zhang, Sheng Bin Hu. The Planar Inlet Design and Analysis Process (PINDAP) is a collection of software tools that allow the efficient aerodynamic design and analysis of planar (two -dimensional and axisymmetric) inlets.

The aerodynamic analysis is performed using the Wind -US computational fluid dynamics (CFD) program. potential. Supersonic convergent-divergent (cd) nozzles are used not only on military jets but also in rocket nozzles and signi cantly on current high speed missiles.

When the gas exits the nozzle at supersonic speeds, it undergoes several ow phenomena depending on the nozzle:pressure ratio (the ratio of inlet to outlet pressure, npr).Cited by: 5. Experimental Investigation of a Fixed-geometry Two-dimensional Mixed-compression Supersonic Inlet with Sweep-forward High- light and Bleed Slot in an Inverted “X”-type Layout Fig.6 illustrates the effects of the Mach number of free stream on the mass flow ratio.

7-coordinate is the ratio of the mass flow ratio at each Mach number to Cited by: 2. • Mass flow inlet. – Used in compressible flows to prescribe mass flow rate at inlet. – Not required for incompressible flows. • Pressure far field. – Available when density is calculated from the ideal gas law.

– Used to model free-stream compressible flow at infinity, with free-stream Mach number and static conditions Size: KB. Consider a two dimensional supersonic air flow over a wall in which there exists a bump, as shown.

A two-dimensional inlet is operating at a flight Mach number of Minfinity= as shown. The flow cross-sectional area at the cowl is Ai= m^2; the cross-sectional area at the location where the norm Engine oil at 40 C flows over a 5-m.

Experiments were conducted in a vacuum-driven supersonic tunnel with nozzles designed to produce Mach or free-stream flow for a continuous run time of five to ten minutes. The test section is inches wide by inches tall and the working fluid consists of conditioned air from the laboratory.

Flow straightening is employedCited by: The flow noise of a sonar platform is one of the main background interferences for sonar applications. This paper focuses on the flow noise of an axisymmetric body in a complex oceanic environment.

Under the condition of a constant stream velocity which comes from the axial direction, an analytical method for computing the flow noise power spectrum in the transition Author: Chunlong Huang, Kunde Yang, Hui Li, Yukun Zhang.

The basic flow field is usually a steady inviscid supersonic flow one, which is the core of the design of a waverider. Basic flow fields used for waverider design can be classified into two types: steady two-dimensional (2D) planar or asymmetrical supersonic flow fields and three-dimensional (3D) supersonic flow : Yao Zheng, Shuai Zhang, Tianlai Gu, Meijun Zhu, Lei Fu, Minghui Chen, Shuai Zhou.estimate of the displacement thickness.

A scramjet inlet is considered as an example application. The predicted results are compared to two-dimensional computational ﬂuid dynamics solutions and experimental results.

Nomenclature a = local sound speed, m=s c = speciﬁc heat, J=kg K H = length normal to ﬂow, m h = speciﬁc enthalpy, J=kg.Librivox Free Audiobook. Fat Tuesday Podcasts.

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