Hostname: page-component-8448b6f56d-m8qmq Total loading time: 0 Render date: 2024-04-23T17:40:44.931Z Has data issue: false hasContentIssue false
  • English
  • Français

Hypervelocity flow of dissociating nitrogen downstream of a blunt nose

Published online by Cambridge University Press:  26 April 2006

M. N. Macrossan
M. N. Macrossan
Affiliation:
Department of Mechanical Engineering, University of Queensland, St. Lucia, Australia
Get access Rights & Permissions [Opens in a new window]

Abstract

The nature of the non-equilibrium flow of strongly dissociating nitrogen has been investigated by a series of simulation calculations using non-equilibrium (finite rate) chemical reactions. These were made with the equilibrium flux method (EFM), and the results have been found to compare favourably with experimental results obtained with a free-piston driven shock-tube wind tunnel which was used to obtain interferograms of the flow of pure nitrogen over a blunt-nosed body, 65 mm long at three angles of incidence. No simple relation between the flow with non-equilibrium chemistry and those for frozen or equilibrium chemistry has been found. The problems of relating test flows produced in the shock tunnel to flight conditions are investigated by considering the test flows that might be produced by some ‘ideal equivalent wind tunnels’. It is shown that the degree of frozen dissociation in the test flow in a shock tunnel is not a serious matter, but that the large difference in Mach number between shock tunnel flows and flight conditions may be more important.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 217 , August 1990 , pp. 167 - 202
Copyright
© 1990 Cambridge University Press

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

Appleton, J. P., Steinberg, M. & Liquornik, D. J. 1968 Shock-tube study of nitrogen dissociation using vacuum-ultraviolet light absorption. J. Chem. Phys. 48, 599.Google Scholar
Baulch, D. L., Drysdale, D. D., Horne, D. G. & Lloyd, A. C. 1973 Evaluated Kinetic Data for High Temperature Reactions. Butterworths.
Bird, G. A. 1976 Molecular Gas Dynamics. Clarendon.
Byron, S. 1966 Shock-tube measurement of the rate of dissociation of nitrogen. J. Chem. Phys. 44, 1378.Google Scholar
Cary, B. 1965 Shock tube study of the thermal dissociation of nitrogen. Phys. Fluids 8, 26.Google Scholar
Crane, K. C. A. & Stalker, R. J. 1977 Mass-spectrometric analysis of hypersonic flows. J. Phys. D: Appl. Phys. 10, 679.Google Scholar
Freeman, N. C. 1958 Non-equilibrium flow of an ideal dissociating gas. J. Fluid Mech. 3, 407.Google Scholar
Griffith, B. J., Maus, J. K., Majors, B. M. & Best, J. T. 1987 Addressing the hypersonic simulation problem. J. Spacecraft 24, 334.Google Scholar
Hanson, R. K. & Baganoff, D. 1972 Shock-tube study of nitrogen dissociation rates using pressure measurements. AIAA J. 10, 211.Google Scholar
Hornung, H. G. 1972 Non-equilibrium dissociating nitrogen flow over spheres and circular cylinders. J. Fluid Mech. 53, 149.Google Scholar
Hornung, H. G. 1976 Non-equilibrium ideal dissociation after a curved shock wave. J. Fluid Mech. 74, 143.Google Scholar
Hornung, H. G. 1988 Experimental real-gas hypersonics. Aero. J. 92, 379.Google Scholar
Kewley, D. J. & Hornung, H. G. 1974 Free-piston shock-tube study of nitrogen dissociation. Chem. Phys. Lett. 25, 531.Google Scholar
Lighthill, M. J. 1957 Dynamics of a dissociating gas. Part 1. Equilibrium flow. J. Fluid Mech. 2, 1.Google Scholar
Macrossan, M. N. 1989 The equilibrium flux method for the calculation of flows with non-equilibrium chemical reactions. J. Comput. Phys. 80, 204.Google Scholar
Macrossan, M. N. & Stalker, R. J. 1987 After-body flow of a dissociating gas down stream of a blunt nose. AIAA paper 87–407.Google Scholar
Marrone, P. V. 1962 Normal shock waves in air. CAL Rep. AG-1729-A-2.
Maus, J. R., Griffith, B. J. & Szema, K. Y. 1984 Hypersonic Mach number and real gas effects on Space Shuttle Orbiter aerodynamics. J. Spacecraft 21, 136.Google Scholar
Mudford, N. R. & Stalker, R. J. 1976 The production of pulsed nozzle flows in a shock tube. AIAA paper 76–357, (AIAA 9th Fluid and Plasma Dynamics Conference, San Diego, Calif.).Google Scholar
Mudford, N. R. & Stalker, R. J. 1980 Hypersonic nozzles for high enthalpy non-equilibrium flow. Aero. Q. 31, 113.Google Scholar
Pullin, D. I. 1980 Direct simulation methods for compressible inviscid ideal gas flow. J. Comput. Phys. 34, 231.Google Scholar
Stalker, R. J. 1989 Approximations for non-equilibrium hypervelocity aerodynamics. AIAA J. (to appear).Google Scholar
Vincenti, W. G. & Kruger, C. H. 1965 An Introduction to Physical Gas Dynamics. Wiley.