Hostname: page-component-848d4c4894-jbqgn Total loading time: 0 Render date: 2024-06-19T15:44:20.076Z Has data issue: false hasContentIssue false
  • English
  • Français

Dimensionless analysis of the unstart boundary for 2D mixed hypersonic inlets

Published online by Cambridge University Press:  03 February 2016

J. Chang ,
D. Yu ,
W. Bao  and
L. Qu
J. Chang
Affiliation:
Harbin Institute of Technology, China
D. Yu
Affiliation:
Harbin Institute of Technology, China
W. Bao
Affiliation:
Harbin Institute of Technology, China
L. Qu
Affiliation:
Harbin Institute of Technology, China
Get access Rights & Permissions [Opens in a new window]

Abstract

Inlet unstart boundary is one of the most important issues of the hypersonic inlet and is also the foundation of the protection control of a scramjet. To solve this problem, the 2D internal steady flow of a 2D mixed internal/external compression hypersonic inlet was numerically simulated at different freestream conditions and backpressures with a RANS (Reynolds-Averaged Navier-Stokes) solver using a RNG (Renormalisation Group) k-ε turbulence model, and two different inlet unstart phenomena were analysed. The dimensional analysis method was introduced to find the essence variables describing the inlet unstart boundary based on “numerical experimental” data in this paper. The dimensionless pressure ratios of the forebody and isolator were analysed respectively. The results show that the unstart boundary of the 2D mixed hypersonic inlet is determined by M0, α and Re0. Pressure ratio π increases with M0 increasing, and it increases firstly and decreases then with α increasing. Pressure ratio π increases with Re0 increasing. Re0 (Re0 < 2 × 107) has a major effect on π and Re0 (Re0 > 2×107) has little effect on π.

Type
Research Article
Information
The Aeronautical Journal , Volume 112 , Issue 1135 , September 2008 , pp. 547 - 555
Copyright
Copyright © Royal Aeronautical Society 2008 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Campbell, D.H., F-12 series aircraft propulsion system performance and development, J of Aircr, 11, (11), 1974, pp 670–676.Google Scholar
2. Seddon, J. and Goldsmith, E.L., Intake Aerodynamics, AIAA Educational Series, AIAA, Washington DC, 1989, pp 149–168.Google Scholar
3. Mayer, D. and Paynter, G.C., Prediction of supersonic inlet unstart caused by freestream disturbances, AIAA J, 33, (2), 1995, pp 266–275.Google Scholar
4. Mayer, D. and Paynter, G.C., Boundary conditions for unsteady supersonic inlet analyses, AIAA J, 32, (6), 1994, pp 1200–1206.Google Scholar
5. Neaves, M.D., McRae, D.S. and Edwards, J.R., High-speed inlet unstart calculations using an implicit solution adaptive mesh algorithm, AIAA Paper 2001-0825, January 2001.Google Scholar
6. Benson, R.A. and McRae, D.S, Numerical simulations of the unstart phenomenon in supersonic inlet/diffuser, AIAA Paper 1993-2239, June 1993.Google Scholar
7. Zha, G.C., Knight, D. and Smith, D., Numerical investigations of high speed civil transport inlet unstart transient at angle of attack, AIAA J of Aircr, 35, (6), 1998, pp 851–856.Google Scholar
8. Zha, G.C., Knight, D. and Smith, D., Numerical simulation of high speed civil transport inlet operability with angle of attack, AIAA J of Aircr, 36, (7), 1998, pp 1223–1229.Google Scholar
9. Cox, C., Lewis, C. and Pap, R., Prediction of unstart phenomena in hypersonic aircraft, AIAA Paper 1995-6018, April 1995.Google Scholar
10. Yu, D., Chang, J., Bao, W. and Xie, Z., Optimal classifications criterions of hypersonic inlet start/unstart, J of Propul and Power, 23, (2), 2007, pp 310–316.Google Scholar
11. Schmitz, D.M. and Bissinger, N.C., Design and testing of fixed-geometry hypersonic intakes, AIAA Paper 1998-1529, April 1998.Google Scholar
12. Van Wie, D.M. and Kwok, F.T., Starting characteristics of supersonic inlets, AIAA Paper 1996-2914, July 1996.Google Scholar
13. Reinartz, B.U. and Herrmann, C.D., Aerodynamic performance analysis of a hypersonic inlet isolator using computation and experiment, J of Propul and Power, 19, (5), 2003, pp 868–875.Google Scholar
14. Emami, S. and Trexler, C.A., Experimental investigation of inlet-combustor isolators for a dual-mode scramjet at a Mach number of 4, NASA Technical Paper 3502, May 1995.Google Scholar
15. Rodriguez, C.G., Computational fluid dynamics analysis of the central institute of aviation motors/NASA scramjet, J of Propul and Power, 19, (4), 2003, pp 547–555.Google Scholar
16. Cui, T., Yu, D., Chang, J. and Bao, W., Topological geometry interpretation of hypersonic inlet start/unstart-catastrophe, hysteresis and bifurcation, AIAA J of Aircr, 45, (4), 2008, pp 1464–1468.Google Scholar
17. Barenblatt, G.I., Dimensional Analysis, Gordon and Breach Science Publishers, New York, 1987.Google Scholar
18. Heiser, W.H. and Pratt, D.T., Hypersonic airbreathing propulsion, AIAA Educational Series, AIAA, Washington DC, 1994, pp 37–39.Google Scholar