Affiliation:
1. Nanjing University of Aeronautics and Astronautics
Abstract
Design methodology of a rectangular variable geometry hypersonic inlet whose cowl lip is translatable along flow direction is clarified in current study and recommendation of key design parameters are given. Unsteady Reynolds-averaged Navier-Stokes (uRANS) calculation were carried out to investigate the feasibility and unsteady aerodynamic characteristics of this inlet. Results indicate that by stretching the movable lip of a model inlet upstream, mass flow rate will increases apparently due to the increases of inlet internal duct entrance area. Stretching the movable lip upstream will decrease CR of the model inlet which is favorable for the start or restart of the inlet from an unstarted status. The lip translating process is smooth and will not induce large amplitude flow disturbance within inlet duct. The movable lip is conducive to improve the aeropropulsive performance of the hypersonic inlet in wide flight range
Publisher
Trans Tech Publications, Ltd.
Reference17 articles.
1. J. Seddon, E. L. GoldSmith, Intake Aerodynamics, 2nd editon. Revised by E. L. GoldSmith, Blackwell Science Ltd, Oxford, (1999).
2. Editors-in-chief: Richard Blockley and Wei Shyy, Encyclopedia of Aerospace Engineering. Volume 2, Propulsion and Power. John Wiley & Sons, Ltd, (2010).
3. Editors-in-chief: Mark Davis. The Standard Handbook for Aeronautical and Astronautical Engineers. McGraw-Hill Standard Handbooks, (2003).
4. Ronald. S. Fry, A Century of Ramjet Propulsion Technology Evolution, Journal of Propulsion and Power, Vol. 20, No. 1, January-February 2004, 27-58.
5. Michael. Zeutzius, Toshiaki. Setoguchi, Kunio. Terao et al, Propulsion System for Hypersonic Space Planes, Journal of Propulsion And Power, Vol. 16, No. 2, March-April 2000, 243-250.