Thrust Losses in Hypersonic Engines Part 1: Methodology

Author

David W. Riggins, Missouri University of Science and TechnologyFollow
C. R. McClinton
P. H. Vitt

Abstract

Expressions for the thrust losses of a scramjet engine are developed in terms of irreversible entropy increases and the degree of incomplete combustion. A method is developed that allows the calculation of the lost engine thrust or thrust potential caused by different loss mechanisms within a given flowfield. This method allows the performance-based assessment of the trade between mixing enhancement and resultant increased flow losses in scramjet combustors. An engine effectiveness parameter for use in optimization of engine components is defined in terms of thrust losses.

Recommended Citation

D. W. Riggins et al., "Thrust Losses in Hypersonic Engines Part 1: Methodology," Journal of Propulsion and Power, American Institute of Aeronautics and Astronautics (AIAA), Jan 1997.

The definitive version is available at https://doi.org/10.2514/2.5160

Department(s)

Mechanical and Aerospace Engineering

International Standard Serial Number (ISSN)

0748-4658

Document Type

Article - Journal

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 1997 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Jan 1997