Numerical Study on Heat-Flow Density of Aerospace Plane

Shuang Chen; Hai Bo Mai

doi:10.4028/www.scientific.net/AMR.900.810

Paper Titles

Theoretical Simulation of the Temperature Increasing Induced by the Friction between Cotton Packages and Iron Floor during the Transportation by Train
p.787

Study on Friction and Wear Behaviors of Aluminium Matrix Composites Reinforced with In Situ Formed TiB₂ Particles
p.794

Study of Analysis Method for Hertz Contact Problem in Friction Drive
p.798

Analysis on the Waste Heat Utilization of Lower Temperature of Steelworks Based on the Theory of Total Energy System
p.805

Numerical Study on Heat-Flow Density of Aerospace Plane
p.810

Numerical Study on Structure Thermal Protection of Aerospace Plane
p.814

Thermal Analysis of Blood Pump Rotor System
p.818

Transient Thermal Analysis of Wheel-Mounted Brake Disc of Gray Cast Iron
p.822

Simulation on Temperature Characteristics of Solar Cell
p.828

HomeAdvanced Materials ResearchAdvanced Materials Research Vol. 900Numerical Study on Heat-Flow Density of Aerospace...

Numerical Study on Heat-Flow Density of Aerospace Plane

Abstract:

Relying on the status of existing thermal protection system and existing flight parameters, appropriate metal thermal protection system being able to reproduced are designed. Then, based on the highest temperature thermal protection materials can bear, flying height of aerospace plane and Mach number, the numerical method was utilized to reveal the heat-flow density of stagnation point on the sharp- nose and the distribution of heat-flow density.

You might also be interested in these eBooks

Advanced Materials and Processing Technologies: IFMPT 2014

View Preview

Info:

Periodical:

Advanced Materials Research (Volume 900)

Pages:

810-813

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.900.810

Citation:

Cite this paper

Online since:

February 2014

Authors:

Shuang Chen*, Hai Bo Mai

Keywords:

Aerodynamic Heating, Aerospace Plane, Hypersonic Speed, Numerical Method, Thermal Protection System

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

* - Corresponding Author

References

[1] Engel C D, Praharaj S C, MINIVER Upgrade for the AVID system, VOLI: LANMIN user's, Aug, 1983NASA CR-1722.

Google Scholar

[2] Zoby E V, J N Moss, K Sutton, Approximate convective heating equations for hypersonic flows, Journal of Spacecraft and Rockets, Vol. 18, NO. 1, 1981: pp.64-70.

DOI: 10.2514/3.57788

Google Scholar

[3] Zoby E V, Simmonds A L T, Engineering flow field method with angle -of-attack applications, Journal of Spacecraft and Rockets, Vol. 22, July-Aug 1985: pp.398-405.

DOI: 10.2514/3.25764

Google Scholar

[4] Christopher J Riley, Application of an engineer in inviscid-boundary layer metrod to slender three-dimensional vehicle forebodies, AIAA-93-2793.

DOI: 10.2514/6.1993-2793

Google Scholar

[5] Weilmuenster K J, Hamilton H H, NASA, 1983 , TP-2103.

Google Scholar

[6] Hamilton H H, Francis A G, Dejarnete F R, Approximate method for calculating heating rates on three-dimensional vehicles, May-June 1994Vol 31, No 3.

Google Scholar