Abstract
The shock cell structures of single supersonic non-ideally expanded jets with arbitrary exit geometry are studied. Both vortex sheets and realistic mean profiles are considered for the jet shear layer. The boundary element method is used to predict the shock spacing and screech tones in a vortex sheet model of a single jet. This formulation enables the calculations to be performed only on the vortex sheet. This permits the efficient and convenient study of complicated jet geometries. Results are given for circular, elliptic and rectangular jets and the results are compared with analysis and experiment. The agreement between the predictions and measurements is very good but depends on the assumptions made to predict the geometry of the fully expanded jet. A finite difference technique is used to examine the effect of finite mixing layer thickness for a single jet. The finite thickness of the mixing layer is found to decrease the shock spacing by approximately 20% over the length of the jet potential core.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 199-211 |
| Number of pages | 13 |
| Journal | Journal of Sound and Vibration |
| Volume | 132 |
| Issue number | 2 |
| DOIs | |
| State | Published - Jul 22 1989 |
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All Science Journal Classification (ASJC) codes
- Condensed Matter Physics
- Acoustics and Ultrasonics
- Mechanics of Materials
- Mechanical Engineering
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A linear shock cell model for jets of arbitrary exit geometry. / Morris, Philip John; Bhat, T. R.S.; Chen, G.
In: Journal of Sound and Vibration, Vol. 132, No. 2, 22.07.1989, p. 199-211.Research output: Contribution to journal › Article
TY - JOUR
T1 - A linear shock cell model for jets of arbitrary exit geometry
AU - Morris, Philip John
AU - Bhat, T. R.S.
AU - Chen, G.
PY - 1989/7/22
Y1 - 1989/7/22
N2 - The shock cell structures of single supersonic non-ideally expanded jets with arbitrary exit geometry are studied. Both vortex sheets and realistic mean profiles are considered for the jet shear layer. The boundary element method is used to predict the shock spacing and screech tones in a vortex sheet model of a single jet. This formulation enables the calculations to be performed only on the vortex sheet. This permits the efficient and convenient study of complicated jet geometries. Results are given for circular, elliptic and rectangular jets and the results are compared with analysis and experiment. The agreement between the predictions and measurements is very good but depends on the assumptions made to predict the geometry of the fully expanded jet. A finite difference technique is used to examine the effect of finite mixing layer thickness for a single jet. The finite thickness of the mixing layer is found to decrease the shock spacing by approximately 20% over the length of the jet potential core.
AB - The shock cell structures of single supersonic non-ideally expanded jets with arbitrary exit geometry are studied. Both vortex sheets and realistic mean profiles are considered for the jet shear layer. The boundary element method is used to predict the shock spacing and screech tones in a vortex sheet model of a single jet. This formulation enables the calculations to be performed only on the vortex sheet. This permits the efficient and convenient study of complicated jet geometries. Results are given for circular, elliptic and rectangular jets and the results are compared with analysis and experiment. The agreement between the predictions and measurements is very good but depends on the assumptions made to predict the geometry of the fully expanded jet. A finite difference technique is used to examine the effect of finite mixing layer thickness for a single jet. The finite thickness of the mixing layer is found to decrease the shock spacing by approximately 20% over the length of the jet potential core.
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U2 - 10.1016/0022-460X(89)90592-0
DO - 10.1016/0022-460X(89)90592-0
M3 - Article
VL - 132
SP - 199
EP - 211
JO - Journal of Sound and Vibration
JF - Journal of Sound and Vibration
SN - 0022-460X
IS - 2
ER -