Author: Herbert S. Glick
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 172
Book Description
Flow Phenomena in Starting a Hypersonic Shock Tunnel
Author: Herbert S. Glick
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 172
Book Description
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 172
Book Description
Fundamental Phenomena in Hypersonic Flow
Author: John Gordon Hall
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 370
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 370
Book Description
The High Temperature Aspects of Hypersonic Flow
Author: Wilbur C. Nelson
Publisher: Elsevier
ISBN: 1483223310
Category : Science
Languages : en
Pages : 801
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.
Publisher: Elsevier
ISBN: 1483223310
Category : Science
Languages : en
Pages : 801
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.
An Investigation Into the Use of an Existing Shock Tube as a Driver for a Hypersonic Shock Tunnel
Author: Michael H. Sherman
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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).
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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).
NASA Technical Note
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 574
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 574
Book Description
A Perfect-gas Analysis of the Expansion Tunnel
Author: Robert L. Trimpi
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 116
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.
Publisher:
ISBN:
Category : Nozzles
Languages : en
Pages : 116
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.
Study of High-density Hypervelocity Flows and Similitudes
Author: Cornell Aeronautical Laboratory
Publisher:
ISBN:
Category : Gas flow
Languages : en
Pages : 320
Book Description
Publisher:
ISBN:
Category : Gas flow
Languages : en
Pages : 320
Book Description
Handbook of Supersonic Aerodynamics
Author: Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 642
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 642
Book Description
Handbook of Supersonic Aerodynamics
Author: I. I. Glass
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 642
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 642
Book Description
Hypersonic Research in the Shock Tunnel
Author: Charles E. Wittliff
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 118
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 118
Book Description