Abstract
This paper presents the design of an efficient, short-length shape transition inlet for hypersonic propulsion systems, operating at Mach 4 to 6. The inlet was shortened by approximately 24 % using a Busemann flow based on the median operating Mach number for streamline-tracing instead of the maximum operating Mach number. Additional upper circular arc of capture shape resulted in a compact compression surface that well preserves internal compression of the Busemann flow, and increased pressure rise by up to 31 % with higher total pressure recovery. The inlet was notched for maximum operating Mach number to minimize air spillage, and the range of operating Mach number and angle of attack was extended. Viscous effects were compensated by a proper truncation angle in order to maintain the exact circular throat shape for efficient manufacturing. The length-reduced inlet showed a wide operating range and high compression performance.
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References
A. Ferri, Review of problems in application of supersonic combustion, The Aeronautical Journal, 68 (645) (1964) 575–597.
A. S. Roudakov, Y. Schickhmann, V. L. Semenov, P. Novelli and O. Fourt, Flight testing an axisymmetric scramjet - Recent Russian advances, 44th Congress of the International Astronautical Federation, Graz, Austria (1993) 485.
A. S. Roudakov, V. L. Semenov, V. I. Kopchenov and J. W. Hicks, Future flight test plans of an axisymmetric hydrogen-fueled scramjet engine on the hypersonic flying laboratory, Space Plane and Hypersonic Systems and Technology Conference, Norfolk, USA (1996) 4572.
M. K. Smart, N. E. Hass and A. Paull, Flight data analysis of the HyShot 2 scramjet flight experiment, AIAA Journal, 44 (10) (2006) 2366–2375.
P. T. Harsha, L. C. Keel, A. Castrogiovanni and R. T. Sherrill, X-43A vehicle design and manufacture, AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference, Capua, Italy (2005) 3334.
J. Kim and J. Shin, Korea’s defense capability and hypersonic weapon system research for nuclear deterrence of North Korea, Korean Political Science Society, 27 (2) (2019) 23–45.
P. Karle and M. P. Boruah, Russia unveils naval doctrine amid navy day celebrations, Jane’s Navy International (2022).
M. Vranic, Tsirkon hypersonic missile hits target at a distance of 1000 km, Jane’s Defence Weekly (2022).
S. N. B. Murthy and E. T. Curran (ed), Scramjet Propulsion, AIAA Inc., Reston, VA (2001).
M. K. Smart, Scramjet Inlets, EN-AVT-185, NATO RTO Educational Notes, NATO (2010).
K. Zhang, Hypersonic Curved Compression Inlet and Its Inverse Design, Springer, Singapore (2020).
J. D. Anderson Jr., A History of Aerodynamics, Cambridge University Press, New York (1997).
J. F. Connors and R. C. Meyers, Design Criteria for Axisymmetric and Two-Dimensional Supersonic Inlets and Exits, NACA-TN-3589, National Advisory Committee for Aeronautics (1956).
C. A. Trexler, Inlet starting predictions for sidewall-compression scramjet inlets, 24th Joint Propulsion Conference, Boston, USA (1988) 3257.
C. A. Trexler, Performance of an inlet for an integrated scramjet concept, Journal of Aircraft, 11 (9) (1974) 589–591.
F. J. Malo-Molina, D. V. Gaitonde and P. H. Kutschenreuter, Numerical investigation of an innovative inward turning inlet, 17th AIAA Computational Fluid Dynamics Conference, Toronto, Canada (2005) 4871.
F. S. Billig, R. A. Baurle, C.-J. Tam and S. F. Wornom, Design and analysis of streamline traced hypersonic inlets, 9th International Space Planes and Hypersonic Systems and Technologies Conference, Norfolk, USA (1999) 4974.
M. K. Smart, Design of three-dimensional hypersonic inlets with rectangular-to-elliptical shape transition, Journal of Propulsion and Power, 15 (3) (1999) 408–416.
F. S. Billig and A. P. Kothari, Streamline tracing: technique for designing hypersonic vehicles, Journal of Propulsion and Power, 16 (3) (2000) 465–471.
A. Busemann, Die achsensymmetrische kegelige Überschallströmung, Luftfahrtforschung, 19 (4) (1942) 137–144.
W. B. Hartill, Analytical and Experimental Investigation of a Scramjet Inlet of Quadriform Shape, AFAPL-TR-65-74, US Air Force (1965).
S. Mölder and E. J. Szpiro, Busemann inlet for hypersonic speeds, Journal of Spacecraft and Rockets, 3 (8) (1966) 1303–1304.
J. L. Kiersey and M. L. Snow, Modular Inlet Investigation, Quarterly Report AQR/66-1, Aeronautics Division, Research and Development, Applied Physics Laboratory, Johns Hopkins University (1966).
P. H. Kutshenreuter, Hypersonic inlet tests in helium and air, AIAA Propulsion Joint Specialist Conference (1965).
J. Seddon and A. Spence, The use of known flow fields as an approach to the design of high speed aircraft, AGARD Conference Proceedings (1968).
S. Z. Pinckney, Rectangular Capture Area to Circular Combustor Scramjet Engine, TM-78657, NASA Langley Research Center (1978).
T. M. Taylor and D. M. Van Wie, Performance analysis of hypersonic shape-changing inlets derived from morphing streamline traced flowpaths, 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (2008) 2635.
S. Mölder, The busemann air intake for hypersonic speeds, G. Pezzella and A. Viviani (ed), Hypersonic Vehicles - Past, Present and Future Developments, IntechOpen, London (2019).
S. Mölder and J. M. Romeskie, Modular Hypersonic Inlets with Conical Flow, AGARD CP-30, McGil University (1968).
M. J. Lewis, A hypersonic propulsion airframe integration overview, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (2003) 4405.
R. J. Gollan and M. K. Smart, Design of modular shape-transition inlets for a conical hypersonic vehicle, Journal of Propulsion and Power, 29 (4) (2013) 832–838.
F. Ding, J. Liu, W. Huang, Y. Zhou and S. Guo, Boundary-layer viscous correction method for hypersonic forebody/inlet integration, Acta Astronautica, 189 (2021) 638–657.
T. W. Drayna, I. Nompelis and G. V. Candler, Hypersonic inward turning inlets: design and optimization, 44th AIAA Aerospace Sciences Meeting and Exhibit (2006) 297.
A. K. Flock and A. Gülhan, Viscous effects and truncation effects in axisymmetric Busemann scramjet intakes, AIAA Journal, 54 (6) (2016) 1881–1891.
H. Ogawa, S. Mölder and R. Boyce, Effects of leading-edge truncation and stunting on drag and efficiency of Busemann intakes for axisymmetric scramjet engines, Journal of Fluid Science and Technology, 8 (2) (2013) 186–199.
M. R. Rosli, M. Takahashi, T. Sato, T. Kojima, H. Taguchi and Y. Maru, Streamline tracing technique based design of elliptical-to-rectangular transitioning hypersonic inlet, 31st AIAA Applied Aerodynamics Conference (2013) 2665.
H. Ogawa, B. Shoesmith, S. Mölder and E. Timofeev, Viscous correction and shock reflection in stunted Busemann intakes, 22nd International Shock Interaction Symposium (2017) 179–196.
S.-W. Cha, T.-S. Roh and H. J. Lee, Comparison of performance on hypersonic intakes in off-design conditions through numerical simulations, Journal of The Korean Society for Aeronautical and Space Sciences, 47 (3) (2019) 195–203.
M. K. Smart and E. G. Ruf, Free-jet testing of a REST scramjet at off-design conditions, 25th AIAA Aerodynamic Measurement Technology and Ground Testing Conference (2006) 2955.
M. K. Smart and C. A. Trexler, Mach 4 performance of hypersonic inlet with rectangular-to-elliptical shape transition, Journal of Propulsion and Power, 20 (2) (2004) 288–293.
W. H. Heiser, D. T. Pratt, D. H. Daley and U. B. Mehta, Hypersonic Airbreathing Propulsion, AIAA Inc., Reston, VA (1994).
J. D. Anderson Jr., Fundamentals of Aerodynamics, McGraw Hill, New York, NY (2011).
The MathWorks, Inc., MATLAB, R2021a, Natick, MA (2021).
L. H. Quan, N. P. Hung, L. D. Quang and V. N. Long, Analysis and design of a scramjet engine inlet operating from Mach 5 to Mach 10, International Journal of Mechanical Engineering and Applications, 4 (1) (2016) 11–23.
Siemens Digital Industries Software, Simcenter STAR-CCM+, Plano, TX (2020).
J. Larsson and S. K. Lele, Direct numerical simulation of canonical shock/turbulence interaction, Physics of Fluids, 21 (12) (2009) 126101.
M. S. Holden, Z. R. Carr, M. MacLean and T. P. Wadhams, Measurements in regions of shock wave/turbulent boundary layer interaction from Mach 4 to 7 at flight duplicated velocities to evaluate and improve the models of turbulence in CFD codes, AIAA Aviation Forum (2018) 3706.
Calspan-University of Buffalo Research Center, Shock Wave/Turbulent Boundary Layer Interaction Study, https://www.cubrc.org/index.php/page/publications (2014) Accessed February 14 2023.
H. Weltens, H. Bressler, F. Terres, H. Neumaier and D. Rammoser, Optimisation of catalytic converter gas flow distribution by CFD prediction, SAE Technical Paper (1993) 930780.
D. M. Van Wie, F. T. Kwok and R. F. Walsh, Starting characteristics of supersonic inlets, 32nd Joint Propulsion Conference and Exhibit (1996) 2914.
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Changwon Lim received his master’s degree from Seoul National University in 2013. He is currently a Ph.D. candidate in the Department of Aerospace Engineering at KAIST and a Senior Researcher at the Agency for Defense Development. His research interests include supersonic and hypersonic propulsion systems.
Sangwook Jin is a Ph.D. candidate in the Department of Aerospace Engineering of KAIST. He is currently a Senior Researcher at the Agency for Defense Development. His research interests include hypersonic air-breathing propulsion systems and high-enthalpy ground tests.
Gisu Park received his Ph.D. degree in 2010 from the University of New South Wales. He is currently an Associate Professor at the Department of Aerospace Engineering of KAIST, Daejeon, Korea. His research interests include hypersonic flows and high-speed ground tests.
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Lim, C., Jin, S. & Park, G. Design and assessment of short-in-length shape transition hypersonic inlet with circular throat. J Mech Sci Technol 37, 6047–6055 (2023). https://doi.org/10.1007/s12206-023-1043-z
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DOI: https://doi.org/10.1007/s12206-023-1043-z