Abstract

Rayleigh scattering has been used to image density cross sections of a compressible boundary layer for the first time to our knowledge. These cross sections were made from a Mach 2.5 boundary layer by illuminating it with a UV laser sheet from an argon–fluoride laser (193 nm). Since Rayleigh scattering is linearly proportional to density, quantitative values are measured, which leads to new instantaneous and statistical information about the structure of this turbulent field.

© 1989 Optical Society of America

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References

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  1. R. B. Miles, D. M. Nosenchuck, “Three-dimensional quantitative flow diagnostics,” in Advances in Fluid Mechanics Measurements, M. Gad-el-Hak, ed., Series on Lecture Notes in Engineering (Springer-Verlag, New York, to be published).
  2. Shardanand, A. D. P. Rao, “Absolute Rayleigh scattering cross sections of gases and Freons of stratospheric interest in the visible and ultraviolet regions,” NASA Tech. Rep. TN D-8442 (National Aeronautics and Space Administration, Washington, D.C., 1987).
  3. T. M. Dyer, AIAA J. 17, 972 (1979).
    [CrossRef]
  4. M. C. Escoda, M. B. Long, AIAA J. 21, 81 (1983).
    [CrossRef]
  5. B. Yip, D. Fourguette, M. B. Long, Appl. Opt. 25, 3919 (1986).
    [CrossRef] [PubMed]
  6. R. Miles, J. Connors, E. Markovitz, P. Howard, G. Roth, Phys. Fluids A 1, 389 (1989).
    [CrossRef]
  7. K. Hayakawa, A. J. Smits, S. M. Bogdonoff, AIAA J. 22, 579 (1984).
    [CrossRef]
  8. E. F. Spina, A. J. Smits, J. Fluid. Mech. 182, 85 (1987).
    [CrossRef]
  9. M. W. Smith, “Cinematic visualization of coherent density structures in a supersonic turbulent boundary layer,” AIAA Paper 88-0500 (American Institute of Aeronautics and Astronautics, New York, 1988).

1989

R. Miles, J. Connors, E. Markovitz, P. Howard, G. Roth, Phys. Fluids A 1, 389 (1989).
[CrossRef]

1987

E. F. Spina, A. J. Smits, J. Fluid. Mech. 182, 85 (1987).
[CrossRef]

1986

1984

K. Hayakawa, A. J. Smits, S. M. Bogdonoff, AIAA J. 22, 579 (1984).
[CrossRef]

1983

M. C. Escoda, M. B. Long, AIAA J. 21, 81 (1983).
[CrossRef]

1979

T. M. Dyer, AIAA J. 17, 972 (1979).
[CrossRef]

Bogdonoff, S. M.

K. Hayakawa, A. J. Smits, S. M. Bogdonoff, AIAA J. 22, 579 (1984).
[CrossRef]

Connors, J.

R. Miles, J. Connors, E. Markovitz, P. Howard, G. Roth, Phys. Fluids A 1, 389 (1989).
[CrossRef]

Dyer, T. M.

T. M. Dyer, AIAA J. 17, 972 (1979).
[CrossRef]

Escoda, M. C.

M. C. Escoda, M. B. Long, AIAA J. 21, 81 (1983).
[CrossRef]

Fourguette, D.

Hayakawa, K.

K. Hayakawa, A. J. Smits, S. M. Bogdonoff, AIAA J. 22, 579 (1984).
[CrossRef]

Howard, P.

R. Miles, J. Connors, E. Markovitz, P. Howard, G. Roth, Phys. Fluids A 1, 389 (1989).
[CrossRef]

Long, M. B.

Markovitz, E.

R. Miles, J. Connors, E. Markovitz, P. Howard, G. Roth, Phys. Fluids A 1, 389 (1989).
[CrossRef]

Miles, R.

R. Miles, J. Connors, E. Markovitz, P. Howard, G. Roth, Phys. Fluids A 1, 389 (1989).
[CrossRef]

Miles, R. B.

R. B. Miles, D. M. Nosenchuck, “Three-dimensional quantitative flow diagnostics,” in Advances in Fluid Mechanics Measurements, M. Gad-el-Hak, ed., Series on Lecture Notes in Engineering (Springer-Verlag, New York, to be published).

Nosenchuck, D. M.

R. B. Miles, D. M. Nosenchuck, “Three-dimensional quantitative flow diagnostics,” in Advances in Fluid Mechanics Measurements, M. Gad-el-Hak, ed., Series on Lecture Notes in Engineering (Springer-Verlag, New York, to be published).

Rao, A. D. P.

Shardanand, A. D. P. Rao, “Absolute Rayleigh scattering cross sections of gases and Freons of stratospheric interest in the visible and ultraviolet regions,” NASA Tech. Rep. TN D-8442 (National Aeronautics and Space Administration, Washington, D.C., 1987).

Roth, G.

R. Miles, J. Connors, E. Markovitz, P. Howard, G. Roth, Phys. Fluids A 1, 389 (1989).
[CrossRef]

Shardanand,

Shardanand, A. D. P. Rao, “Absolute Rayleigh scattering cross sections of gases and Freons of stratospheric interest in the visible and ultraviolet regions,” NASA Tech. Rep. TN D-8442 (National Aeronautics and Space Administration, Washington, D.C., 1987).

Smith, M. W.

M. W. Smith, “Cinematic visualization of coherent density structures in a supersonic turbulent boundary layer,” AIAA Paper 88-0500 (American Institute of Aeronautics and Astronautics, New York, 1988).

Smits, A. J.

E. F. Spina, A. J. Smits, J. Fluid. Mech. 182, 85 (1987).
[CrossRef]

K. Hayakawa, A. J. Smits, S. M. Bogdonoff, AIAA J. 22, 579 (1984).
[CrossRef]

Spina, E. F.

E. F. Spina, A. J. Smits, J. Fluid. Mech. 182, 85 (1987).
[CrossRef]

Yip, B.

AIAA J.

T. M. Dyer, AIAA J. 17, 972 (1979).
[CrossRef]

M. C. Escoda, M. B. Long, AIAA J. 21, 81 (1983).
[CrossRef]

K. Hayakawa, A. J. Smits, S. M. Bogdonoff, AIAA J. 22, 579 (1984).
[CrossRef]

Appl. Opt.

J. Fluid. Mech.

E. F. Spina, A. J. Smits, J. Fluid. Mech. 182, 85 (1987).
[CrossRef]

Phys. Fluids A

R. Miles, J. Connors, E. Markovitz, P. Howard, G. Roth, Phys. Fluids A 1, 389 (1989).
[CrossRef]

Other

R. B. Miles, D. M. Nosenchuck, “Three-dimensional quantitative flow diagnostics,” in Advances in Fluid Mechanics Measurements, M. Gad-el-Hak, ed., Series on Lecture Notes in Engineering (Springer-Verlag, New York, to be published).

Shardanand, A. D. P. Rao, “Absolute Rayleigh scattering cross sections of gases and Freons of stratospheric interest in the visible and ultraviolet regions,” NASA Tech. Rep. TN D-8442 (National Aeronautics and Space Administration, Washington, D.C., 1987).

M. W. Smith, “Cinematic visualization of coherent density structures in a supersonic turbulent boundary layer,” AIAA Paper 88-0500 (American Institute of Aeronautics and Astronautics, New York, 1988).

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Figures (5)

Fig. 1
Fig. 1

Streamwise density cross section normal to the boundary. The streamwise field of view is approximately 3δ (12.6 mm).

Fig. 2
Fig. 2

Density cross sections parallel to the boundary at (a) y/δ = 0.84 and (b) y/δ = 0.60.

Fig. 3
Fig. 3

Probability distribution functions of density at a series of y/δ locations.

Fig. 4
Fig. 4

Two-dimensional spatial correlations of density around a reference point near the middle of the boundary layer.

Fig. 5
Fig. 5

Mach 2.5 boundary layer riding over a 16° wedge. The bright region near the boundary is scattering from the wedge model

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