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Author: Richard T. Driftmyer Publisher: ISBN: Category : Flow visualization Languages : en Pages : 62
Book Description
The report describes the results of an experimental study involving a two-dimensional, underexpanded, free jet flowing into a static medium. The investigation was concerned with the determination of jet heights as a function of the nozzle flow properties. In support of this objective experimental results of two supersonic nozzles (Mach numbers of 2.89 and 2.99 and throat widths of 0.0335 inch and 0.0204 inch, respectively) are presented along with a complete data tabulation which includes photographs. A universal data correlation, expanded to include the axisymmetric jet case, is presented.
Author: Richard T. Driftmyer Publisher: ISBN: Category : Flow visualization Languages : en Pages : 62
Book Description
The report describes the results of an experimental study involving a two-dimensional, underexpanded, free jet flowing into a static medium. The investigation was concerned with the determination of jet heights as a function of the nozzle flow properties. In support of this objective experimental results of two supersonic nozzles (Mach numbers of 2.89 and 2.99 and throat widths of 0.0335 inch and 0.0204 inch, respectively) are presented along with a complete data tabulation which includes photographs. A universal data correlation, expanded to include the axisymmetric jet case, is presented.
Author: Michael J Werle Publisher: ISBN: Category : Jets Languages : en Pages : 174
Book Description
The report describes the results of an experimental study concerning the injection of a gaseous secondary jet into an unbounded supersonic flow field which was uniform outside of a turbulent boundary layer. The investigation was principally concerned with the definition of the proper scale length to be associated with turbulent two-dimensional jet-interaction flows. In support of this objective, results are presented for a Mach 4 test conducted using a flat-plate model containing a sonic secondary jet directed normal to the mainstream. Secondary jet strengths were varied from approximately 0 to 1000 for jet throat sizes of 0.005 inch, 0.020 inch and 0.030 inch. The jet interaction phenomenon was studied using detailed surface pressure distributions measured fore and aft of the secondary jet in conjunction with comprehensive shadowgraph coverage of the interaction flow field. (Author).
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development Publisher: ISBN: Category : Aeronautics Languages : en Pages : 594
Author: Richard T. Driftmyer
Author: Richard T. Driftmyer
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Author: Michael J Werle
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Author: Frank L. Clark
Author: Jet Propulsion Laboratory (U.S.)
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Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development
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