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Performance Improvement of a Supersonic External Compression Inlet by Heat Source Addition

Authors: Mohammad Reza Soltani, Mohammad Farahani, Javad Sepahi Younsi

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

Digital Object Identifier (DOI): doi.org/10.5281/zenodo.1057233

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References:


[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.