APPLYING THE METHOD OF CHARACTERISTICS TO ANALYZE THE FLOW FIELD OF A CHEMICALLY REACTING GAS IN A TWO-DIMENSIONAL OR AN AXISYMMETRIC NOZZLE

1965 ◽  
Author(s):  
Roger R. Craig
Keyword(s):  
Flow Field ◽  
Method Of Characteristics ◽  
Two Dimensional ◽  
Axisymmetric Nozzle ◽  
The Method Of Characteristics ◽  
Chemically Reacting

Boundary Layer Closure and Heat Transfer in Constant Base Pressure and Simple Wave Guns

1978 ◽  
Vol 100 (4) ◽  
pp. 690-696 ◽  
Author(s):  
A. D. Anderson ◽  
T. J. Dahm
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Layer Thickness ◽  
Boundary Layer Thickness ◽  
Method Of Characteristics ◽  
Simple Wave ◽  
Momentum Equation ◽  
Base Pressure ◽  
Two Dimensional ◽  
The Method Of Characteristics

Solutions of the two-dimensional, unsteady integral momentum equation are obtained via the method of characteristics for two limiting modes of light gas launcher operation, the “constant base pressure gun” and the “simple wave gun”. Example predictions of boundary layer thickness and heat transfer are presented for a particular 1 in. hydrogen gun operated in each of these modes. Results for the constant base pressure gun are also presented in an approximate, more general form.

scholarly journals Calculation of the horizontal two-dimensional unsteady flows by the method of characteristics

2003 ◽  
Vol 25 (1) ◽  
pp. 49-64
Author(s):  
Tran Gia Lich ◽  
Nguyen Minh Son ◽  
Le Viet Cuong
Keyword(s):  
Numerical Experiments ◽  
Method Of Characteristics ◽  
Unsteady Flows ◽  
Equation System ◽  
Characteristic Form ◽  
Two Dimensional ◽  
The Method Of Characteristics ◽  
Venant Equation

This paper will be concerned with the characteristic form of the two dimensional Saint-Venant equation system, the supplementary equations at the boundaries, the methods of characteristics for solving the equation system and some numerical experiments.

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

1991 ◽  
Vol 113 (3) ◽  
pp. 479-488 ◽  
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.

Supersonic Nozzle Design

1946 ◽  
Vol 13 (4) ◽  
pp. A265-A270 ◽  
Author(s):  
A. E. Puckett
Keyword(s):  
Flow Field ◽  
Method Of Characteristics ◽  
Supersonic Nozzle ◽  
Approximate Solutions ◽  
Two Dimensional ◽  
Nozzle Design ◽  
Small Areas ◽  
Engineering Problems ◽  
Two Dimensional Flow ◽  
Flow Changes

Abstract A two-dimensional flow field in which the velocity is everywhere supersonic can always be represented approximately by a number of small adjacent quadrilateral flow fields in each of which the velocity and pressure are constant. These quadrilaterals must be separated by lines representing waves in the flow; changes in velocity and pressure through any wave can be computed. By increasing the number of small areas into which the complete flow field is divided, the accuracy of this approximate solutions may be increased without limit. This constitutes the “method of characteristics” solution, which has been known for many years. This method may be applied to the graphical computation of flow in a supersonic nozzle, with the particular aim of producing uniform supersonic flow at the end of the nozzle. It is pointed out that such a computation is essentially simple and rapid, and its essential features are presented in a form which, it is hoped, may be easily applied to engineering problems.

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