A Semi-Quantitative Schlieren High-Speed Flow Diagnostic: Analysis of High-Pressure-Ratio, Overexpanded Planar Flow in Rocket Nozzles

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Thorsett-Hill, K. (2012). A Semi-Quantitative Schlieren High-Speed Flow Diagnostic: Analysis of High-Pressure-Ratio, Overexpanded Planar Flow in Rocket Nozzles. Unc Charlotte Electronic Theses And Dissertations.
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Abstract

This work introduces a semi-quantitative schlieren (SQS) method which is used to qualitatively and quantitatively analyze complex, unsteady, compressible flows in a small, planar convergent-divergent nozzle. A basic schlieren system is used to image the evolution in time of complex supersonic flow structures, including Prandtl-Meyer expansion fans, internal shocks, near-wall oblique shocks, quasi-normal shocks, shock/boundary layer interactions, shock/shock interactions, and shock trains. The first images of shock trains in high nozzle-pressure-ratio flows are shown, and the underlying processes are described. A flow-field decomposition method is presented which allows the entire flow field to be separated into unit processes and analyzed. Various methods of analysis are presented, including a new method for the determination of node locations along a defined nozzle wall geometry using the method of characteristics. A numerical solution is developed for the analysis of a blow-down process. Computer programs which implement these solutions are presented.

Details
Author

Thorsett-Hill, Karen

Title

A Semi-Quantitative Schlieren High-Speed Flow Diagnostic: Analysis of High-Pressure-Ratio, Overexpanded Planar Flow in Rocket Nozzles

Physical Description

1 online resource (133 pages) : PDF

Date

2012

Degree Granting Institution

University of North Carolina at Charlotte

Abstract

This work introduces a semi-quantitative schlieren (SQS) method which is used to qualitatively and quantitatively analyze complex, unsteady, compressible flows in a small, planar convergent-divergent nozzle. A basic schlieren system is used to image the evolution in time of complex supersonic flow structures, including Prandtl-Meyer expansion fans, internal shocks, near-wall oblique shocks, quasi-normal shocks, shock/boundary layer interactions, shock/shock interactions, and shock trains. The first images of shock trains in high nozzle-pressure-ratio flows are shown, and the underlying processes are described. A flow-field decomposition method is presented which allows the entire flow field to be separated into unit processes and analyzed. Various methods of analysis are presented, including a new method for the determination of node locations along a defined nozzle wall geometry using the method of characteristics. A numerical solution is developed for the analysis of a blow-down process. Computer programs which implement these solutions are presented.

Genre

doctoral dissertations

Subjects--Topics

Mechanical engineering

Degree

Ph.D.

Keywords

High Pressure Ratio
Nozzle
Rocket
Semi-Quantitative Schlieren
Shockwave

Subject Area

Mechanical Engineering

Advisor(s)

Keanini, Russell

Committee Members

Tkacik, Peter
Weggel, David
Kakad, Yogendra

Degree Note

Thesis (Ph.D.)--University of North Carolina at Charlotte, 2012.

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Rights Holder Information

Copyright is held by the author unless otherwise indicated.

Identifier

ThorsettHill_uncc_0694D_10382

Permalink

http://hdl.handle.net/20.500.13093/etd:409