![]() E., “ Detection and Analysis of Shock-Like Waves Emitted by Heated Supersonic Jets Using Shadowgraph Flow Visualization,” Journal of the Acoustical Society of America, Vol. 136, No. 4, 2014, Paper 2101. doi: EXFLDU 0723-4864 Crossref Google Scholar N., “ Quantitative Schlieren Measurements of Coherent Structures in a Cavity Shear Layer,” Experiments in Fluids, Vol. 30, No. 2, Feb. 2001, pp. 123–134. doi: JFLSA7 0022-1120 Crossref Google Scholar R., “ Coherence Between Large-Scale Jet-Mixing Structure and its Pressure Field,” Journal of Fluid Mechanics, Vol. 116, March 1982, pp. 31–57. doi: JSVIAG 0022-460X Crossref Google Scholar and Tournois G., “ Acoustic Velocimetry Measurement in the Air by means of Laser Doppler Velocimetry: Dynamics and Frequency Range Limitations and Signal Processing Improvements,” Journal of Sound and Vibration, Vol. 229, No. 3, 2000, pp. 607–626. and Jordan P., “ The Near Pressure Field of Co-Axial Subsonic Jets,” Journal of Fluid Mechanics, Vol. 611, Sept. 2008, pp. 175–204. N., “ The Proper Orthogonal Decomposition of Pressure Fluctuations Surrounding a Turbulent Jet,” Journal of Fluid Mechanics, Vol. 340, June 1997, pp. 1–33. doi: AIAJAH 0001-1452 Link Google Scholar F., “ Coalescence in the Sound Field of a Laboratory-Scale Supersonic Jet,” AIAA Journal, Vol. 54, No. 1, 2016, pp. 254–265. The findings reveal quantitative evidence of the sources of most intense vibroacoustic loads during the end-effects regime of clustered rockets. Radon transforms of the spatially resolved shadowgraphy images are then used to characterize the statistical behavior of the acoustic wave fronts that reside within the hydrodynamic periphery of the nozzle flow. The exhaust plumes and surrounding sound field are first visualized by way of retroreflective shadowgraphy. These end-effects regime pulsations produce significant vibroacoustic loads due to the intermittent breathing of the last trapped annular separation bubble with the ambient. The second condition is at a nozzle pressure ratio of 37 and is when the flow and internal shock pattern transition rapidly between free-shock separated flow and the end-effects regime. The first condition is at a nozzle pressure ratio of 25, at which point the flow is in a restricted-shock separated state. A nonintrusive measure of the exhaust plume and immediate sound field produced by a cluster of two thrust-optimized parabolic contour nozzles is studied during two steady-state conditions. ![]()
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |