Mole-fraction-sensitive imaging of hypermixing shear layers

J. S. Fox; A. F.P. Houwing; P. M. Danehy; M. J. Gaston; N. R. Mudford; S. L. Gai

doi:10.2514/2.5775

Mole-fraction-sensitive imaging of hypermixing shear layers

J. S. Fox, A. F.P. Houwing, P. M. Danehy, M. J. Gaston, N. R. Mudford, S. L. Gai

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26 Citations (Scopus)

Abstract

A theoretical model that determines the optimum excitation frequency for obtaining a fluorescence signal with a strong dependence on fuel mole fraction is presented for supersonic fuel-air compressible mixing studies. The challenge associated with this is to maintain a high sensitivity to fuel mole fraction with minimal sensitivity to temperature and pressure in a flow with large temperature variations and pressure gradients. The results of the model are applied to the mixing region behind various scramjet fuel injectors in a shock tunnel to measure fuel mole fraction. Hydrogen fuel at a Mach number of 1.7 is injected into a mostly N₂ freestream at Mach 4.8. Experimental fluorescence images are presented in streamwise and spanwise planes.

Original language	English
Pages (from-to)	284-292
Number of pages	9
Journal	Journal of Propulsion and Power
Volume	17
Issue number	2
DOIs	https://doi.org/10.2514/2.5775
Publication status	Published - 2001

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title = "Mole-fraction-sensitive imaging of hypermixing shear layers",

abstract = "A theoretical model that determines the optimum excitation frequency for obtaining a fluorescence signal with a strong dependence on fuel mole fraction is presented for supersonic fuel-air compressible mixing studies. The challenge associated with this is to maintain a high sensitivity to fuel mole fraction with minimal sensitivity to temperature and pressure in a flow with large temperature variations and pressure gradients. The results of the model are applied to the mixing region behind various scramjet fuel injectors in a shock tunnel to measure fuel mole fraction. Hydrogen fuel at a Mach number of 1.7 is injected into a mostly N2 freestream at Mach 4.8. Experimental fluorescence images are presented in streamwise and spanwise planes.",

author = "Fox, {J. S.} and Houwing, {A. F.P.} and Danehy, {P. M.} and Gaston, {M. J.} and Mudford, {N. R.} and Gai, {S. L.}",

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AU - Fox, J. S.

AU - Houwing, A. F.P.

AU - Danehy, P. M.

AU - Gaston, M. J.

AU - Mudford, N. R.

AU - Gai, S. L.

PY - 2001

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AB - A theoretical model that determines the optimum excitation frequency for obtaining a fluorescence signal with a strong dependence on fuel mole fraction is presented for supersonic fuel-air compressible mixing studies. The challenge associated with this is to maintain a high sensitivity to fuel mole fraction with minimal sensitivity to temperature and pressure in a flow with large temperature variations and pressure gradients. The results of the model are applied to the mixing region behind various scramjet fuel injectors in a shock tunnel to measure fuel mole fraction. Hydrogen fuel at a Mach number of 1.7 is injected into a mostly N2 freestream at Mach 4.8. Experimental fluorescence images are presented in streamwise and spanwise planes.

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JO - Journal of Propulsion and Power

JF - Journal of Propulsion and Power

IS - 2

ER -

Mole-fraction-sensitive imaging of hypermixing shear layers

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