Experimental results of a Mach 10 conical-flow derived waverider to 14-X hypersonic aerospace vehicle

Rolim, Tiago Cavalcanti; Toro, Paulo Gilberto de Paula; Minucci, Marco Antonio Sala; Oliveira, Antônio de Carlos de; Follador, Roberto da Cunha

doi:10.5028/jatm.2011.03027510

Abstract

This paper presents a research in the development of the 14-X hypersonic airspace vehicle at Institute for Advanced Studies (IEAv) from Department of Science and Aerospace Technology (DCTA) of the Brazilian Air Force (FAB). The 14-X project objective is to develop a higher efficient satellite launch alternative, using a Supersonic Combustion Ramjet (SCRAMJET) engine and waverider aerodynamics. For this development, the waverider technology is under investigation in Prof. Henry T. Nagamatsu Aerothermodynamics and Hypersonics Laboratory (LHTN), in IEAv/DCTA. The investigation has been conducted through ground test campaigns in Hypersonic Shock Tunnel T3. The 14-X Waverider Vehicle characteristic was verified in shock tunnel T3 where surface static pressures and pitot pressure for Mach number 10 were measured and, using Schlieren photographs Diagnostic Method, it was possible to identify a leading-edge attached shock wave in 14-X lower surface.

Keywords:
Hypersonics; Hypersonic systems; Shock tunnel; Schlieren; Waverider

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REFERENCES

Anderson, J. D., 1991, "Fundamentals of Aerodynamics", New York , MacGraw-Hill, 2^nd Edition.
Anderson, J. D., 1989, "Hypersonic and High Temperature Gas Dynamics", New York , McGraw-Hill.
Bertin, J. J., 1994, "Hypersonic Aerothermodynamics", New York, AIAA Education Series.
Hayes, W. D. and Probstein, R. F., 1959, "Hypersonic Flow Theory", New York, Academic Press.
Heiser, W. H., et al., 1994, "Hypersonic Airbreathing Propulsion", AIAA Education Series.
Javaid, K. H., Serghides, V. C., 2005, "Airframe Propulsion Integration Methodology for Waverider Derived Hypersonic Cruise Aircraft Design Concepts", Journal of Spacecraft and Rockets, AIAA, No. 5 , Vol. 42. , pp. 663-671.
Kim, B. S., Rasmussen, M. L., Jischke, M. S., 1983, "Optimization of Waverider Configurations Generated from Axisymmetric Conical Flows" Journal of Spacecraft, AIAA, No. 5 , Vol. 20. , pp. 461-469.
Minucci, M. A. S., 1991, "Experimental Investigation of 2-D Scramjet Inlet at Flow Mach Numbers 8 to 25 and Stagnation Temperature of 800K to 4100K", Ph.D. dissertation, Aeronautical Engineering Dept. Ressenlaer Polytechnique Institute, Troy, NY.
Nagamatsu, H. T., Sheer, R. E. Jr, 1961, "Hypersonic Shock Wave-Boundary layer Interaction and Leading Edge Slip", American Rocket Society Journal, No. 5, Vol. 30, pp. 454-462.
Nagamatsu, H.T., Li., T. Y., 1960, "Hypersonic Viscous Flow Near the Leading Edge of a Flat Plate" Physics of Fluid., No. 1, Vol. 3, pp. 140-141.
Nonweiler, T. R. F., 1963, "Delta wings of Shape Amenable to Exact Shock Wave Theory", Journal of the Royal Aeronautical Society, Vol. 67, p. 39.
O'neill, M. K., Lewis, M. D., 1992, "Optimized Scramjet Integration on a Waverider", Journal of Aircraft, AIAA, No. 6 , Vol. 29, pp. 1114-1121.
Rasmussen, M. L., He, X., 1990, "Analysis of Cone-Derived Waveriders by Hypersonic Small-Disturbance Theory", Proceedings of the First International Hypersonic Waverider Symposium.
Rault, D. F. G., 1994, "Aerodynamic Characteristics of Hypersonic Viscous Optimized Waverider at High Altitudes", Journal of Spacecraft and Rockets, No. 5, Vol. 31, pp. 719-727.
Toro, P. G. P., et al, 1998, "Hypersonic Flow Over a Flat Plate", 36th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV.
Wang, Y., Zhang, D., Deng, X., 2007, "Design of Waverider Configuration with High Lift-Drag Ratio" Journal of Aircraft, No. 1, Vol. 44, pp. 144-148.

Publication Dates

Publication in this collection
May-Aug 2011

History

Received
14 June 2010
Accepted
11 July 2011

This is an Open Access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

[1] Anderson, J. D., 1991, "Fundamentals of Aerodynamics", New York , MacGraw-Hill, 2^nd Edition.

[2] Anderson, J. D., 1989, "Hypersonic and High Temperature Gas Dynamics", New York , McGraw-Hill.

[3] Bertin, J. J., 1994, "Hypersonic Aerothermodynamics", New York, AIAA Education Series.

[4] Hayes, W. D. and Probstein, R. F., 1959, "Hypersonic Flow Theory", New York, Academic Press.

[5] Heiser, W. H., et al., 1994, "Hypersonic Airbreathing Propulsion", AIAA Education Series.

[6] Javaid, K. H., Serghides, V. C., 2005, "Airframe Propulsion Integration Methodology for Waverider Derived Hypersonic Cruise Aircraft Design Concepts", Journal of Spacecraft and Rockets, AIAA, No. 5 , Vol. 42. , pp. 663-671.

[7] Kim, B. S., Rasmussen, M. L., Jischke, M. S., 1983, "Optimization of Waverider Configurations Generated from Axisymmetric Conical Flows" Journal of Spacecraft, AIAA, No. 5 , Vol. 20. , pp. 461-469.

[8] Minucci, M. A. S., 1991, "Experimental Investigation of 2-D Scramjet Inlet at Flow Mach Numbers 8 to 25 and Stagnation Temperature of 800K to 4100K", Ph.D. dissertation, Aeronautical Engineering Dept. Ressenlaer Polytechnique Institute, Troy, NY.

[9] Nagamatsu, H. T., Sheer, R. E. Jr, 1961, "Hypersonic Shock Wave-Boundary layer Interaction and Leading Edge Slip", American Rocket Society Journal, No. 5, Vol. 30, pp. 454-462.

[10] Nagamatsu, H.T., Li., T. Y., 1960, "Hypersonic Viscous Flow Near the Leading Edge of a Flat Plate" Physics of Fluid., No. 1, Vol. 3, pp. 140-141.

[11] Nonweiler, T. R. F., 1963, "Delta wings of Shape Amenable to Exact Shock Wave Theory", Journal of the Royal Aeronautical Society, Vol. 67, p. 39.

[12] O'neill, M. K., Lewis, M. D., 1992, "Optimized Scramjet Integration on a Waverider", Journal of Aircraft, AIAA, No. 6 , Vol. 29, pp. 1114-1121.

[13] Rasmussen, M. L., He, X., 1990, "Analysis of Cone-Derived Waveriders by Hypersonic Small-Disturbance Theory", Proceedings of the First International Hypersonic Waverider Symposium.

[14] Rault, D. F. G., 1994, "Aerodynamic Characteristics of Hypersonic Viscous Optimized Waverider at High Altitudes", Journal of Spacecraft and Rockets, No. 5, Vol. 31, pp. 719-727.

[15] Toro, P. G. P., et al, 1998, "Hypersonic Flow Over a Flat Plate", 36th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV.

[16] Wang, Y., Zhang, D., Deng, X., 2007, "Design of Waverider Configuration with High Lift-Drag Ratio" Journal of Aircraft, No. 1, Vol. 44, pp. 144-148.

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