Flow Phenomena in Starting a Hypersonic Shock Tunnel PDF Download
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Author: Herbert S. Glick
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 172
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Book Description
Author: Herbert S. Glick
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 172
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Book Description
Author: John Gordon Hall
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 370
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Book Description
Author: Wilbur C. Nelson
Publisher: Elsevier
ISBN: 1483223310
Category : Science
Languages : en
Pages : 801
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Book Description
The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.
Author: Michael H. Sherman
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
This thesis describes experiments carried out using an existing tube alone, and with the tube connected to two-dimensional wedge nozzle. The range of maximum duration of steady reflected pressure from 3.5 to 5 milliseconds was achieved through tailored operation for incident shock strengths of 3.4 and 2.0, using pure Helium and a 70% Helium/30% Nitrogen mixture as the driver gas respectfully. Spark and continuous light shadowgraph techniques were attempted using an optical window at the Mach 4.3 location. Results demonstrated that the short duration flow phenomena in a shock tunnel can be recorded successfully using existing equipment. Calculations showed that the addition of a Mach 10 nozzle and 15 cu m (6' diameter x 15' long) dump chamber would provide a useful hypersonic facility for instruction and research. (KR).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 574
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Book Description
Author: Robert L. Trimpi
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 116
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Book Description
A perfect-gas analysis is presented for an apparatus consisting of a basic expansion tube at the downstream end of which a nozzle has been added. The resultant tube at the downstream end of which a nozzle has been added. The resultant apparatus, named the expansion tunnel, is shown to have the following advantages when compared with the basic expansion tube: increased testing time, larger initial test-gas slug length, higher efficiency, and reduced secondary-diaphgram bursting problems. Principal disadvantages are requirement of an additional nozzle, and the requirement disadvantages are requirement of an additional nozzle, and the requirement of a larger ratio between maximum and minimum pressures in an operating cycle. Authors conclude inherent advantages more than compensate for disadvantages.
Author: Cornell Aeronautical Laboratory
Publisher:
ISBN:
Category : Gas flow
Languages : en
Pages : 320
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Book Description
Author: Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 642
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Book Description
Author: I. I. Glass
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 642
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Book Description
Author: Charles E. Wittliff
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 118
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Book Description
