Basic Supersonic Ramjet Point-Design Performance
ResearchPublished 1955
A study which may serve as an aid to propulsion engineers concerned with preliminary missile design in estimating ramjet performance. Thrust coefficients and specific impulses from Mach 1.3 to 5.0 are presented for a wide variation in engine component efficiencies. Hydrocarbon is the only fuel type considered.
Document Details
- Copyright: RAND Corporation
- Availability: Available
- Year: 1955
- Print Format: Paperback
- Paperback Pages: 57
- Paperback Price: $23.00
- Document Number: RM-1615
Citation
RAND Style Manual
Chicago Manual of Style
Young, G. B. W., Basic Supersonic Ramjet Point-Design Performance, RAND Corporation, RM-1615, 1955. As of September 23, 2024: https://www.rand.org/pubs/research_memoranda/RM1615.html
Young, G. B. W., Basic Supersonic Ramjet Point-Design Performance. Santa Monica, CA: RAND Corporation, 1955. https://www.rand.org/pubs/research_memoranda/RM1615.html. Also available in print form.
This publication is part of the RAND research memorandum series. The research memorandum series, a product of RAND from 1948 to 1973, included working papers meant to report current results of RAND research to appropriate audiences.
This document and trademark(s) contained herein are protected by law. This representation of RAND intellectual property is provided for noncommercial use only. Unauthorized posting of this publication online is prohibited; linking directly to this product page is encouraged. Permission is required from RAND to reproduce, or reuse in another form, any of its research documents for commercial purposes. For information on reprint and reuse permissions, please visit www.rand.org/pubs/permissions.
RAND is a nonprofit institution that helps improve policy and decisionmaking through research and analysis. RAND's publications do not necessarily reflect the opinions of its research clients and sponsors.