Emendation of the Brown & Michael equation, with application to sound generation by vortex motion near a half-plane

Journal of Fluid Mechanics

Volumn 329, Issue , 1996, Pages 89-101

  Howe, M S ^a  

^a Boston University   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

ACOUSTIC WAVES; PARTIAL DIFFERENTIAL EQUATIONS; REYNOLDS NUMBER; VORTEX SHEDDING; WAKES;

BROWN AND MICHAEL EQUATION; KUTTA CONDITION;

VORTEX FLOW;

EID: 0030388722     PISSN: 00221120     EISSN: None     Source Type: Journal    
DOI: 10.1017/S002211209600883X     Document Type: Article

References (28)

1. BROWN, C. E. & MICHAEL, W. H. 1954 Effect of leading edge separation on the lift of a delta wing. J. Aero. Sci. 21, 690-706.
2. BROWN, C. E. & MICHAEL, W. H. 1955 On slender delta wings with leading-edge separation. NACA Tech. Note 3430.
3. CHANDIRAMANI, K. L. 1974 Diffraction of evanescent waves, with applications to aerodynamically scattered sound and radiation from unbaffled plates. J. Acoust. Soc. Am. 55, 19-29.
4. CHASE, D. M. 1972 Sound radiated by turbulent flow off a rigid half-plane as obtained from a wavevector spectrum of hydrodynamic pressure. J. Acoust. Soc. Am. 52, 1011-1023.
5. CHASE, D. M. 1975 Noise radiated from an edge in turbulent flow. AIAA J. 13, 1041-1047.
6. CLEMENTS, R. R. 1973 An inviscid model of two-dimensional vortex shedding. J. Fluid Mech. 57, 321-336.
7. CORTELEZZI, L. & LEONARD, A. 1993 Point vortex model for the unsteady separated flow past a semiinfinite plate with transverse motion. Fluid. Dyn. Res. 11, 263-295.
8. CORTELEZZI, L., LEONARD, A. & DOYLE, J. C. 1994 An example of active circulation control of the unsteady separated flow past a semi-infinite plate. J. Fluid Mech. 260, 127-154.
9. CRIGHTON, D. G. 1972 Radiation from vortex filament motion near a half plane. J. Fluid Mech. 51, 357-362.
10. CRIGHTON, D. G. & LEPPINGTON, F. G. 1970 Scattering of aerodynamic noise by a semi-infinite compliant plate. J. Fluid Mech. 43, 721-736.
11. CRIGHTON, D. G. & LEPPINGTON, F. G. 1971 On the scattering of aerodynamic noise. J. Fluid Mech. 46, 577-597.
12. CURLE, N. 1955 The influence of solid boundaries upon aerodynamic sound. Proc. R. Soc. Lond. A 231, 505-514.
13. DORE, B. D. 1966 Nonlinear theory for slender wings in sudden plunging motion. Aeronaut. Q. 17, 187-200.
14. FFOWCS WILLIAMS, J. E. & HALL, L. H. 1970 Aerodynamic sound generation by turbulent flow in the vicinity of a scattering half-plane. J. Fluid Mech. 40, 657-670.
15. GRAHAM, J. M. R. 1980 The forces on the sharp-edged cylinders in oscillatory flow at low Keulegan-Carpenter numbers. J. Fluid Mech. 97, 331-346.
16. HOWE, M. S. 1975 Contributions to the theory of aerodynamic sound, with application to excess jet noise and the theory of the flute. J. Fluid Mech. 71, 625-673.
17. HOWE, M. S. 1989 On unsteady surface forces, and sound produced by the normal chopping of a rectilinear vortex. J. Fluid Mech. 206, 131-153.
18. LIGHTHILL, M. J. 1952 On sound generated aerodynamically. Part I: General theory. Proc. R. Soc. Lond. A 211, 564-587.
19. LOWSON, M. V. 1963 The separated flow on slender wings in unsteady motion. Reports & Memoranda of the Aeronautical Research Council, no. 3448.
20. MANGLER, K. W. & SMITH, J. H. B. 1959 A theory for the flow past a slender delta wing with leading edge separation. Proc. R. Soc. Lond. A 251, 200-217.
21. MORSE, P. M. & FESHBACH, H. 1953 Methods of Theoretical Physics, vols. 1 and 2. McGraw-Hill.
22. PETERS, M. C. A. M. 1993 Aeroacoustic sources in internal flows. PhD thesis, Eindhoven University of Technology.
23. PETERS, M. C. A. M. & HIRSCHBERG, A. 1993 Acoustically induced periodic vortex shedding at sharp edged open channel ends: simple vortex models. J. Sound Vib. 161, 281-299.
24. RANDALL, D. G. 1966 Oscillating slender wings with leading edge separation. Aeronaut. Q. 17, 311-331.
25. ROTT, N. 1956 Diffraction of a weak shock with vortex generation. J. Fluid Mech. 1, 111-128.
26. SMITH, J. H. B. 1959 A theory of the separated flow from the curved leading edge of a slender wing. Reports & Memoranda of the Aeronautical Research Council, no. 3116.
27. SMITH, J. H. B. 1968 Improved calculations of leading edge separation from slender, thin, delta wings. Proc. R. Soc. A 306, 67-90.
28. TAVARES, T. S. & MCCUNE, J. E. 1993 Aerodynamics of maneuvering slender wings with leading edge separation AIAA J. 31, 977-986.