Access the full text.
Sign up today, get DeepDyve free for 14 days.
M. Chiaverini, George Harting, Y. Lu, K. Kuo, A. Peretz, H. Jones, Brian Wygle, J. Arves (1999)
Pyrolysis Behavior of Hybrid-Rocket Solid Fuels Under Rapid Heating ConditionsJournal of Propulsion and Power, 15
Zhuo Chang-fe (2014)
Numerical Research on Drag Reduction of Base Bleed in Supersonic Flow
(2014)
Effect of base bleed type on drag reduction performance in supersonic flow
H. Heaton, W. Reynolds, W. Kays (1964)
HEAT TRANSFER IN ANNULAR PASSAGES. SIMULTANEOUS DEVELOPMENT OF VELOCITY AND TEMPERATURE FIELDS IN LAMINAR FLOWInternational Journal of Heat and Mass Transfer, 7
(1999)
SFRJ used on minor-diameter ammunition
R. Baurle, T. Mathur, M. Gruber, K. Jackson (1998)
A numerical and experimental investigation of a scramjet combustor for hypersonic missile applications
R. Veraar, A. Mayer (2005)
The Role of the TNO-PML Free Jet Test Facility in Solid Fuel Ramjet Projectile Development
(1995)
A computer program for flight performance prediction of solid fuel ramjet propelled projectiles
S. Krishnan, Philmon George (1998)
Solid Fuel Ramjet Combustor DesignProgress in Aerospace Sciences, 34
R. Veraar, K. Andersson (2001)
Flight test results of the Swedish-Dutch solid fuel ramjet propelled projectile
(1996)
Solid fuel ramjet (SFRJ) propulsion for kinetic energy penetrator applications-progress to date
(1993)
Initial study of a 40mm SFRJ projectile
(2006)
Solid fuel ramjet projectiles-the conceptual structure, progress to date and development prediction
The purpose of this paper is to study the operation performance of the high-speed ramjet kinetic energy projectile using solid fuel ramjet as power plant that is a new short-range and small caliber projectile.Design/methodology/approachThe numerical investigation on combustion characteristic of polyethylene in high-speed ramjet kinetic energy projectile is carried out in this paper. The flow characteristics’ differences are analyzed when ramjet works or do not work, and both the combustion characteristics and propulsive performance are analyzed when ramjet works.FindingsThe results show that with the increase of the abscissa x, the flame front is close to solid fuel surface at first and then keeps away from solid fuel surface. With the increase of the abscissa x, the temperature of solid fuel surface and regression rate of solid fuel continues to increase before re-attachment point and then decreases, which a maximum locate at the re-attachment point. Both the average temperature and the regression rate on the surface of the solid fuel tend to rise as the increase of inflow Mach number. As the inflow of Mach number increases, the mass flow rate of gaseous fuel increases.Practical implicationsThe research results can provide useful database for the subsequent research on high-speed ramjet kinetic energy projectile.Originality/valueThis paper studies the operation characteristics of the ramjet projectile, especially the effect of the change of the flight velocity on the performance of high-speed ramjet projectile.
Aircraft Engineering and Aerospace Technology: An International Journal – Emerald Publishing
Published: Aug 15, 2019
Keywords: Computational fluid dynamics; Combustion characteristic; Kinetic energy projectile; Solid fuel ramjet
Read and print from thousands of top scholarly journals.
Already have an account? Log in
Bookmark this article. You can see your Bookmarks on your DeepDyve Library.
To save an article, log in first, or sign up for a DeepDyve account if you don’t already have one.
Copy and paste the desired citation format or use the link below to download a file formatted for EndNote
Access the full text.
Sign up today, get DeepDyve free for 14 days.
All DeepDyve websites use cookies to improve your online experience. They were placed on your computer when you launched this website. You can change your cookie settings through your browser.