International Journal of Aeronautical and Space Sciences

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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A Study on Blended Inlet Body Design for a High Supersonic Unmanned Aerial Vehicle

  • You, Lianxing (Key Laboratory of Fundamental Science for National Defense Advanced Design Technology of Flight Vehicle, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics) ;
  • Yu, Xiongqing (Key Laboratory of Fundamental Science for National Defense Advanced Design Technology of Flight Vehicle, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics) ;
  • Li, Hongmei (Department of Automation Engineering, Nanjing Institute of Mechatronic Technology)
  • Received : 2015.07.10
  • Accepted : 2016.05.29
  • Published : 2016.06.30
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Abstract

The design process of blended inlet body (BIB) for the preliminary design of a near-space high supersonic unmanned aerial vehicle (HSUAV) is presented. The mass flow rate and cowl area of inlet at a design point are obtained according to the cruise condition of the HSUAV. A mixed-compression axisymmetric supersonic inlet section with a fixed geometry reasonably matching the high supersonic cruise state is created by using the inviscid theory of aerodynamics. The inlet section is optimized and used as a baseline section for the BIB design. Three BIB concepts for the HSUAV are proposed, and their internal aerodynamic characteristics of inlet are evaluated using Euler computational fluid dynamics (Euler CFD) solver. The preferred concept is identified, in which the straight leading edge of the baseline HSUAV configuration is modified into the convex leading edge to accommodate the inlet and meet the requirements of the cowl area to capture the sufficient air flow. The total recovery of inlet for the preferred BIB concept and the aerodynamic characteristics of the modified HSUAV configuration are verified using Navier-Stokes computational fluid dynamics (NS CFD) solver. The validation indicates that the preferred BIB concept can meet both the requirements of the inlet and aerodynamic performance of the HSUAV.

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References

  1. Curran, E. T. and Murthy, S. N. B., Scramjet Propulsion, American Institute of Aeronautics and Astronautics, Inc., Reston, Virginia, 2000, pp. 449
  2. Segal, C., The Scramjet Engine Processes and Characteristics, Cambridge University Press, New York, 2009, pp. 1-86.
  3. Orbital Science Corporation, "D-21B RBCC Modification Feasibility Study", NASA TM-15296, 1999.
  4. Tomaro, R. F. and Wurtzler, K. E., "High-speed configuration aerodynamics: SR-71 to SMV", 17th Applied Aerodynamics Conference, AIAA 1999-3204, 1999.
  5. Ross, J. W. and Rogerson, D. B., "XB-70 technology advancements", AIAA 1983-1048, 1983.
  6. Scharnhorst, R. K., "An Overview of Military Aircraft Supersonic Inlet Aerodynamics", 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, AIAA 2012-0013, 2012.
  7. Mahoney, J. J., Inlets for Supersonic Missiles, American Institute of Aeronautics and Astronautics, Inc., Washington, DC, 1990, pp. 23-230.
  8. Seddon, S. and Goldsmith, E. L., Intake Aerodynamics, American Institute of Aeronautics and Astronautics, Inc., Washington, DC, 1985, pp. 20-350.
  9. Fry, R. S., "A Century of Ramjet Propulsion Technology Evolution", Journal of Propulsion and Power, Vol. 20, No. 1, 2004, pp. 27-58. https://doi.org/10.2514/1.9178
  10. Anderson, Jr, J. D., Fundamentals of Aerodynamics Fifth Edition, McGraw-Hill Companies, Inc., New York, NY, 2011, pp. 513-668.
  11. Van der Velden, A., Koch, P. and Wujek, B., "iSIGHTFD, a Tool for Multi-Objective Data Analysis", 12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, AIAA 2008-5988, 2008.
  12. Jack, D.M., Hans von O., Elements of Propulsion: Gas Turbines and Rockets, American Institute of Aeronautics and Astronautics, Inc., Reston, Virginia, 2006, pp. 266-277.
  13. Jack, D.M., William, H.H. and David, T.P., Aircraft Engine Design Second Edition, American Institute of Aeronautics and Astronautics, Inc., Reston, Virginia, 2002, pp. 120.
  14. Lei, W., Kunyuan, Z., Xiangjun, N., Lin, Z., Ninggang, G. and Yongzhou, L., "Optimization and Experimental Investigation of 2-D Hypersonic Curved Shock Compression Inlet", 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, AIAA 2012-5959, 2012.
  15. Van Wie, D. M., Kwok, F. T. and Walsh, R. F., "Starting characteristics of supersonic inlets", 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, AIAA 96-2914, 1996.
  16. Gordon, C. O., Aircraft Propulsion Systems Technology and Design, American Institute of Aeronautics and Astronautics, Inc., Washington, DC, 1989, pp. 203-212.
  17. Dyer, J. D., Hartfield, R. J., Dozier, G. V. and Burkhalter, J. E., "Aerospace Design Optimization Using a Steady State Real-coded Genetic Algorithm", Applied Mathematics and Computation, Vol. 218, Issue 9, 2012, pp. 4710-4730. https://doi.org/10.1016/j.amc.2011.07.038
  18. Ahuja, V. and Hartfield, D. R., "Optimization of Airbreathing Hypersonic Aircraft Design for Maximum Cruise Speeds Using Genetic Algorithms", 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, AIAA 2009-7323, 2009.
  19. Kuchemann, D., the Aerodynamic Design of Aircraft, American Institute of Aeronautics and Astronautics, Inc., Reston, Virginia, 2012, pp. 352.
  20. Hsia, Y. C., Gross, B. and Ortwerth, J. P., "Inviscid Analysis of a Dual Mode Scramjet Inlet", Journal of Propulsion and Power, Vol. 7, No. 6, 1989, pp. 1030-1035. https://doi.org/10.2514/3.23423
  21. Coratekin, T., van Keuk J. and Ballmann, J., "Preliminary Investigations in 2D and 3D Ramjet Inlet design", 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA 99-2667, 1999.
  22. Milne, M. E. and Arthur, M. T., "Evaluation of bespoke and commercial CFD methods for UCAV configuration", 24th Applied Aerodynamics Conference, AIAA 2006-2988, 2006.