Paper Titles

Analysis of Ecological of Characteristic Time for Thermoacoustic Refrigerator by Double Acoustic Drivers
p.313

Kinematics and Dynamics Simulation of L-10/7 Piston Type Air Compressor with Double Actions
p.319

The Transmission Design and Production of Cylindrical Cam and Gear Joint Transmission Reducer
p.323

Based on 3D Virtual Prototype Technology and Finite Element Analysis of the Optimization of the Automobile Front Axle
p.330

Research on the Protection of Forward-Facing Cavity on the Flow Field of Low Total Pressure Opposing Jet
p.335

Based on Analysis of Finite Element Analysis of Automobile Transmission Shaft Comprehensive Optimization
p.341

Three-Dimensional Finite Element Coupled Analysis of a Diesel Engine Piston
p.347

The Research on Virtual Prototype of Rod-Cone Docking Mechanism
p.354

Axial Deformation of the Planetary Differential Micro-Displacement Mechanism with Finite Element Analysis
p.358

HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 684Research on the Protection of Forward-Facing...

Research on the Protection of Forward-Facing Cavity on the Flow Field of Low Total Pressure Opposing Jet

Article Preview

Abstract:

This paper focus on the detailed influence of forward-facing cavity on the opposing jet. The flow field of a hemisphere nose-tip with the combined configuration was simulated numerically and the surface heat flux distribution was obtained. The numerical results show that a suitable cavity is helpful for the opposing jet. With the same total pressure, the single opposing jet even can’t form a stable flow field and there is no cooling effect.

You might also be interested in these eBooks

Proceedings of 2014 International Conference on Mechanics and Mechanical Engineering

Info:

Periodical:

Applied Mechanics and Materials (Volume 684)

Pages:

335-340

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.684.335

Citation:

Cite this paper

Online since:

October 2014

Authors:

Hai Bo Lu*, Leng Han

Keywords:

Flow Field, Forward-Facing Cavity, Opposing Jet, Thermal Protection System

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

© 2014 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

* - Corresponding Author

[1] D. G. Bogard, K. A. Thole, Gas Turbine Film Cooling, AIAA J. of Propulsion and Power, 22 (2006) 249-270.

DOI: 10.2514/1.18034

[2] Zhang F, Liu WQ, Analysis of Thermal Wrinkling Resulted from Non-uniform Temperature Distribution in Transpiration Cooling Formed Platelets, Acta Aeronautica et Astronautica Sinica 28 (2007) 138-142.

[3] M. Yanauchi, K. Fujii, Numerical Investigation of Supersonic Flows around a Spiked Blunt Body, Journal of Spacecraft and Rockets, 32(1995) 32-42.

DOI: 10.2514/3.26571

[4] Xiao-yi Han, Jun Wang, Effect of Mach number on thermoelectric performance of SiC ceramics nose-tip for supersonic vehicles, Applied Thermal Engineering, 62(2014) 141-147.

DOI: 10.1016/j.applthermaleng.2013.09.011

[5] C. H. E. Warren, An Experimental investigation of the effect of ejecting a coolant gas at the nose of a bluff body, Journal of Fluid Mechanics, 8(1960) 400-417.

DOI: 10.1017/s0022112060000694

[6] K. Hayashi, S. Aso, Effect of Pressure Ratio on Aerodynamic Heating Reduction due to Opposing Jet, AIAA 2003-4041 (2003).

DOI: 10.2514/6.2003-4041

[7] T. Tian, C. Yan, Numerical simulation on opposing jet in hypersonic flow, Journal of Beijing University of Aeronautics and Astronautics, 34(2008) 9-12.

[8] I. Tamada, S. Aso, Y. Tani, Reducing Aerodynamic Heating by the Opposing Jet in Supersonic and Hypersonic Flows, AIAA 2010-991 (2010).

DOI: 10.2514/6.2010-991

[9] K. Hayashi, S. Aso, Y. Tani, Numerical Study of Thermal Protection System by Opposing Jet, AIAA 2005-188 (2005).

DOI: 10.2514/6.2005-188

[10] P. B. Burbank, R. L. Stallings, Heat-Transfer and Pressure Measurements on a Flat Nose Cylinder at a Mach Number Range of 2. 49 to 4. 44, NASA TM X-221 (1959).

[11] B. Yuceil, D. S. Dolling, D. Wilson, A Preliminary Investigation of the Helmholtz Resonator Concept for Heat Flux Reduction, AIAA 1993-2742 (1993).

DOI: 10.2514/6.1993-2742

[12] S. Saravanan, G. Jagadeesh, K. P. J. Reddy, Investigation of Missile-Shaped Body with Forward- Facing Cavity at Mach 8, J. Spacecraft and Rockets, 46(2009) 577-591.

DOI: 10.2514/1.38914

[13] Hai-Bo Lu, Wei-Qiang Liu, Investigation of the thermal protection efficiency of hypersonic vehicle with forward-facing cavity, Journal of Astronautics, 33(2012) 1013-1018.

[14] Hai-Bo Lu, Wei-Qiang Liu, Cooling efficiency investigation of forward-facing cavity and opposing jet combinatorial thermal protection system, Acta Phys. Sin. 61(2012) 064703.

DOI: 10.7498/aps.61.064703

[15] Hai-bo Lu, Wei-qiang Liu, Forward-facing Cavity and Opposing Jet Combined Thermal Protection System, Thermophysics and Aeromechanics, 19(2012) 561-569.

DOI: 10.1134/s086986431204004x

[16] Lu Haibo, Liu Weiqiang, Investigation of thermal protection system by forward-facing cavity and opposing jet combinatorial configuration, Chinese Journal of Aeronautics, 26(2013) 287-293.

DOI: 10.1016/j.cja.2013.02.005

[17] Hai-Bo Lu, Wei-Qiang Liu, Research on thermal protection mechanism of forward-facing cavity and opposing jet combinatorial thermal protection system, Heat Mass Transfer 50(2014) 449-456.

DOI: 10.1007/s00231-013-1247-3

[18] Chen L Z. Numerical Simulation and Research of the Unsteady Separation Flows around Double-Delta Wings, Ph.D. thesis, China Aerodynamics Research and Development Center, (2008).