Performance Improvement of a Supersonic External Compression Inlet by Heat Source Addition
Heat source addition to the axisymmetric supersonic
inlet may improve the performance parameters, which will increase
the inlet efficiency. In this investigation the heat has been added to
the flow field at some distance ahead of an axisymmetric inlet by
adding an imaginary thermal source upstream of cowl lip. The effect
of heat addition on the drag coefficient, mass flow rate and the
overall efficiency of the inlet have been investigated. The results
show that heat addition causes flow separation, hence to prevent this
phenomena, roughness has been added on the spike surface.
However, heat addition reduces the drag coefficient and the inlet
mass flow rate considerably. Furthermore, the effects of position,
size, and shape on the inlet performance were studied. It is found that
the thermal source deflects the flow streamlines. By improper
location of the thermal source, the optimum condition has been
obtained. For the optimum condition, the drag coefficient is
considerably reduced and the inlet mass flow rate and its efficiency
have been increased slightly. The optimum shape of the heat source
is obtained too.
[1] J. Roskam, Airplane Design, Part 6. Ottawa: Roskam Aviation and
engineering Corporation, 1987, pp. 159-164.
[2] E. L. Goldsmith, J. Seddon, Practical Intake Aerodynamic Design.
London: Blackwell Scientific Publications, 1993.
[3] H. Kobayash et al., "Study on variable-shape supersonic inlets and
missiles with MRD device," ScienceDirect, 2006, pp. 1-11.
[4] S. O. Macheret, M. N. Shneider, R. B. Miles, "Scramjet inlet control by
off-body energy addition: a virtual cowl," 41st AIAA Aerospace
Sciences Meeting and Exhibit, Reno, Jan. 2003, pp. 1-19.
[5] I. G. Girgis, M. N. Shneider, S. O. Macheret, G. L. Brown, R. B. Miles,
" Steering moments creation in supersonic flow by off-axis plasma heat
addition," Journal of Spacecraft and Rockets, vol. 43, no. 3, May-June
2006, pp. 607-613.
[6] B. McAndrew, J. Kline, R. B. Miles, "Aerodynamic control of a
symmetric cone in compressible flow using microwave driven plasma
discharges," 41st AIAA Aerospace Sciences Meeting and Exhibit, Reno,
Jan. 2003, pp. 1-8.
[7] R. B. Miles et al., "Plasma control of shock waves in aerodynamics and
sonic boom mitigation," 32nd AIAA Plasmadynamics and Lasers Conf.
and 4th Weakly Ionized Gases Workshop Conf. & Exhibit, Anaheim,
CA, June 2001, pp. 1-13.
[8] K. Kremeyer, "Lines of pulsed energy for supersonic/hypersonic drag
reduction: generation and implementation," AIAA-2004-0984, 2004, pp.
1-11.
[9] M. R. Soltani, M. Taiebi-Rahni, M. Farahani, M. R. Heidari, "Flow
measurements around a long axisymmetric body with varying cross
section," AIAA-05-50, 2005.
[1] J. Roskam, Airplane Design, Part 6. Ottawa: Roskam Aviation and
engineering Corporation, 1987, pp. 159-164.
[2] E. L. Goldsmith, J. Seddon, Practical Intake Aerodynamic Design.
London: Blackwell Scientific Publications, 1993.
[3] H. Kobayash et al., "Study on variable-shape supersonic inlets and
missiles with MRD device," ScienceDirect, 2006, pp. 1-11.
[4] S. O. Macheret, M. N. Shneider, R. B. Miles, "Scramjet inlet control by
off-body energy addition: a virtual cowl," 41st AIAA Aerospace
Sciences Meeting and Exhibit, Reno, Jan. 2003, pp. 1-19.
[5] I. G. Girgis, M. N. Shneider, S. O. Macheret, G. L. Brown, R. B. Miles,
" Steering moments creation in supersonic flow by off-axis plasma heat
addition," Journal of Spacecraft and Rockets, vol. 43, no. 3, May-June
2006, pp. 607-613.
[6] B. McAndrew, J. Kline, R. B. Miles, "Aerodynamic control of a
symmetric cone in compressible flow using microwave driven plasma
discharges," 41st AIAA Aerospace Sciences Meeting and Exhibit, Reno,
Jan. 2003, pp. 1-8.
[7] R. B. Miles et al., "Plasma control of shock waves in aerodynamics and
sonic boom mitigation," 32nd AIAA Plasmadynamics and Lasers Conf.
and 4th Weakly Ionized Gases Workshop Conf. & Exhibit, Anaheim,
CA, June 2001, pp. 1-13.
[8] K. Kremeyer, "Lines of pulsed energy for supersonic/hypersonic drag
reduction: generation and implementation," AIAA-2004-0984, 2004, pp.
1-11.
[9] M. R. Soltani, M. Taiebi-Rahni, M. Farahani, M. R. Heidari, "Flow
measurements around a long axisymmetric body with varying cross
section," AIAA-05-50, 2005.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:51579", author = "Mohammad Reza Soltani and Mohammad Farahani and Javad Sepahi Younsi", title = "Performance Improvement of a Supersonic External Compression Inlet by Heat Source Addition", abstract = "Heat source addition to the axisymmetric supersonic
inlet may improve the performance parameters, which will increase
the inlet efficiency. In this investigation the heat has been added to
the flow field at some distance ahead of an axisymmetric inlet by
adding an imaginary thermal source upstream of cowl lip. The effect
of heat addition on the drag coefficient, mass flow rate and the
overall efficiency of the inlet have been investigated. The results
show that heat addition causes flow separation, hence to prevent this
phenomena, roughness has been added on the spike surface.
However, heat addition reduces the drag coefficient and the inlet
mass flow rate considerably. Furthermore, the effects of position,
size, and shape on the inlet performance were studied. It is found that
the thermal source deflects the flow streamlines. By improper
location of the thermal source, the optimum condition has been
obtained. For the optimum condition, the drag coefficient is
considerably reduced and the inlet mass flow rate and its efficiency
have been increased slightly. The optimum shape of the heat source
is obtained too.", keywords = "Drag coefficient, heat source, performanceparameters, supersonic inlet.", volume = "2", number = "4", pages = "401-8", }