An Experimental Investigation Of Supersonic Rectangular Over Expanded Nozzle Of Single And Two Phase Flows PDF Download
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Author | : |
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Total Pages | : 109 |
Release | : 2008 |
Genre | : |
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Download An Experimental Investigation of Supersonic Rectangular Over-expanded Nozzle of Single and Two-phase Flows Book in PDF, ePub and Kindle
This dissertation presents the results of an experimental investigation and analysis of the supersonic rectangular over-expanded flow of single and two-phase flows. Recent interest in rectangular supersonic jets is motivated by the need to reduce plume length and acoustically excited structural loads in the exhaust system of high performance aircrafts. Semi-periodic shock structures form in the jet plumes of these vehicles during low speed flight at off design conditions. These shock cells affect the jet velocity and temperature decay as well as the jet spread rate and its acoustic field. The flow regimes and shock structure in the plume was characterized for jets in quiescent atmosphere at over-expanded conditions. Instantaneous and phase average schlieren/shadowgraph images of the internal flow and the jets are presented to show the over-expanded shock structure and jet spread rate at different nozzle pressure ratios ranged from 1.6 to 9.5. A high-pressure particle feeders have been constructed to steady feed the dispersed large particles and the seeding particle for LDA measurements at different particle loading rates. Schlieren pictures of the jets are presented to show the shock structure and jet spread rate. LDV measurements are presented for the jet flow field and the centerline velocity decay. The results indicate that the rectangular supersonic jet spread rate is greater along the minor axis and increases with the nozzle pressure ratio. The individual shock cell length, as well as, the total number of shock cells within the jet plume were found to increase with nozzle pressure ratio. In two-phase rectangular jets of gas and dispersed solid particles the shock strength was found to attenuate with increased particle loading. The design, construction and initial shakedown of the facility has been accomplished. The effort required to reach this stage has been greater than initially expected. Further more detailed data acquisitions and measurements will be accomplished in future studies.
Author | : Gary L. Barr |
Publisher | : |
Total Pages | : 118 |
Release | : 1972 |
Genre | : Rockets (Aeronautics) |
ISBN | : |
Download Experimental Investigation of the Sudden Expansion of Supersonic Flow Into a 90 ̊vee Shaped Channel Book in PDF, ePub and Kindle
Author | : John Dill McKenney |
Publisher | : |
Total Pages | : 31 |
Release | : 1949 |
Genre | : |
ISBN | : |
Download An Investigation of Flow Separation in an Overexpanded Supersonic Nozzle Book in PDF, ePub and Kindle
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 46 |
Release | : 2018-07-12 |
Genre | : |
ISBN | : 9781722830243 |
Download Supersonic Investigation of Two Dimensional Hypersonic Exhaust Nozzles Book in PDF, ePub and Kindle
An experimental investigation was conducted in the NASA Lewis 10 x 10 ft supersonic Wind Tunnel to determine the performance characteristics of 2D hypersonic exhaust nozzles/afterbodies at low supersonic conditions. Generally, this type of application requires a single expansion ramp nozzle (SERN) that is highly integrated with the airframe of the hypersonic vehicle. At design conditions (hypersonic speeds), the nozzle generally exhibits acceptable performance. At off-design conditions (transonic to mid-supersonic speeds), nozzle performance of a fixed geometry configuration is generally poor. Various 2-D nozzle configurations were tested at off-design conditions from Mach 2.0 to 3.5. Performance data is presented at nozzle pressure ratios from 1 to 35. Jet exhaust was simulated with high-pressure air. To study performance of different geometries, nozzle configurations were varied by interchanging the following model parts: internal upstream contour, expansion ramp, sidewalls, and cowl. Carboni, Jeanne D. and Shyne, Rickey J. and Leavitt, Laurence D. and Taylor, John G. and Lamb, Milton Glenn Research Center; Langley Research Center RTOP 763-01-21...
Author | : Jain-Ming Wu |
Publisher | : |
Total Pages | : 10 |
Release | : 1970 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Experimental Investigation of Supersonic Flow Separation Over a Rearward Facing Step Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 868 |
Release | : 2008 |
Genre | : Dissertations, Academic |
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Download Dissertation Abstracts International Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 702 |
Release | : 1995 |
Genre | : Aeronautics |
ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
Author | : Ning Zhuang |
Publisher | : |
Total Pages | : 176 |
Release | : 2007 |
Genre | : |
ISBN | : |
Download Experimental Investigation of Supersonic Cavity Flows and Their Control Book in PDF, ePub and Kindle
The study of supersonic cavity flows is of interest both from fundamental fluid dynamics and practical perspectives. The complex nature of this flowfield, consisting of compressible shear layers, compression/expansion waves, and fluid-acoustic interactions, makes it a rich problem to study. A detailed experimental study of supersonic flow (M=1.5 to 2) over a range of three-dimensional rectangular cavities (L/D=1 to 5.2) was conducted. The measurements included unsteady surface pressure measurements, particle image velocimetry, and flow visualization using shadowgraph and schlieren. Large-scale structures in the shear layer and a large recirculation zone in the cavity was observed. Spatial and temporal mode switching was also observed, the nature being different for short and long cavities. The shear layer characteristics of the two cavities are very different in term of curvature and growth. Supersonic microjets were used at the leading edge of the cavities to suppress the resonance in the flow. With a minimal mass flux (0.15%), the activation of microjets led to a large reduction in cavity tones (20 dB) and overall sound pressure levels (9dB). In addition, the microjet injection enhanced the shear layer mixing and reduced the velocity fluctuation in the cavities. The significant reductions together with the low mass flux requirements make this a potentially viable technique for full-scale, practical applications.
Author | : Edward Malcolm Harvey Newton |
Publisher | : |
Total Pages | : 100 |
Release | : 1964 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Experimental Investigation of Supersonic Flow in the Neighborhood of a Forward-facing Step Book in PDF, ePub and Kindle
Author | : Thomas Johani |
Publisher | : |
Total Pages | : 142 |
Release | : 1968 |
Genre | : |
ISBN | : |
Download An Experimental Investigation of Boundary Layer Expansion Around a Convex Corner in Supersonic Flow Book in PDF, ePub and Kindle