Wind Tunnel Testing Facilities at the Ballistic Research Laboratories PDF Download
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Author: J. C. McMullen
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
Author: J. C. McMullen
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
Author:
Publisher:
ISBN:
Category : Ballistics
Languages : en
Pages : 38
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Author:
Publisher:
ISBN:
Category : Supersonic wind tunnels
Languages : en
Pages : 36
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 504
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Book Description
Author: J. C. McMullen
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 38
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Author: Bain Dayman
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 112
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Author: Clarence C. Bush
Publisher:
ISBN:
Category :
Languages : en
Pages : 52
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Book Description
The Ballistic Research Laboratories' Supersonic Wind Tunnel No. 1 flow characteristics are presented in detail to assist those who may wish to make use of the facility. Techniques and instrumentation used i calibrating supersonic nozzles for Mach number and flow direction distributions are discussed, as well as nozzle adjustment procedures used to improve the flow in the tsting region for nozzles with flexible walls. (Author).
Author: Anders S. Platou
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 54
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Book Description
It has been found that good quality, low turbulence flow in a wind tunnel test section is dependent on the flow and turbulence conditions in the supply header. This report indicates how good quality, low turbulence flow can be obtained in a supply header and presents flow surveys taken in a supply header before and after modification. (Author).
Author: Charles J. Nietubicz
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Book Description
Results of the vapor screen technique development in the Ballistic Research Laboratories Supersonic Wind Tunnel No. 1 are presented. A standard light source in conjunction with a schlieren mirror system are compared photographically with the results of using a laser light source. The amount of condensation required, photographic equipment and testing procedure are presented. Vapor screen pictures of main body vortices, photographed through a downstream prism as well as through the tunnel access window are shown. A unique photograph showing a set of vortices being generated prior to separation is presented. The wind tunnel tests were conducted at Mach number 2.25. (Author).
Author: Maurice A. Sylvester
Publisher:
ISBN:
Category : Launch vehicles (Astronautics)
Languages : en
Pages : 44
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