Design of axisymmetric supersonic/hypersonic nozzles

Desai, SS and Viswanathan, S (1980) Design of axisymmetric supersonic/hypersonic nozzles. Technical Report. National Aeronautical Laboratory, Bangalore, India.

Full text available as:
[img] PDF
Restricted to Archive staff only

Download (3509Kb)

    Abstract

    A method is given here for the design of axisymmetric13; supersonic/hypersonic nozzles. The final nozzle contour is13; obtained by adding the boundary-layer displacement to the inviscid contour. Method of characteristics is used in obtaining the inviscid contour. The initial data required to start the scheme of method of characteristics is in the form of Mach number distribution along the nozzle axis. Certain improvements are made to the unified approach of Sivells for obtaining a consistent and smooth distribution of Mach number along the nozzle axis. Equations are derived for calculating the mass flow across a characteristic between two field points. As a result of these relations it has been possible to locate the wall-streamline more accurately in the numerical work than by the previously existing methods.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Supersonic nozzle;Hypersonic nozzle;Contour;Axisymmetric
    Subjects: AERONAUTICS > Aerodynamics
    Division/Department: Aerodynamics, Aerodynamics
    Depositing User: Mr. Ravikumar R
    Date Deposited: 30 Aug 2006
    Last Modified: 24 May 2010 09:50
    URI: http://nal-ir.nal.res.in/id/eprint/2607

    Actions (login required)

    View Item