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Title: Conceptual design and performance estimates for a supersonic aerodynamic window for the ATA vacuum system aperature. Final report. [Advanced Test Accelerator]

Abstract

A family of supersonic aerodynamic window devices for the ATA aperture have been examined. These included transverse supersonic jet flows of the compression window type, the expansion window type, and an extended expansion window type, as well as an axial supersonic ejector type window. The pure compression type window was rejected because it would require a nozzle exit Mach number exceeding 8.5 to support an attached shock wave. The pure expansion window is optimized at an exit Mach number of unity, but requires 4 times the mass flow rate of the pure compression window, and would probably be unstable at M/sub e/ < 1.5 to 2.0. The extended expansion window was found to require mass flows of the same order as the pure compression window, but is optimized at M/sub e/ approx. = 3. The supersonic ejector would require two stages each having an exit Mach number exceeding 6 to achieve mass flow rates competitive with the extended expansion window. In addition, it appears very doubtful that an efficient ejector could be designed within the overall length limitation. Ejector designs which might meet the length limitation will probably require substantially (2 to 3 times) higher mass flow rates than themore » extended expansion window. Therefore, the supersonic transverse extended-expansion window (STEW) is considered the preferred design. At an exit Mach number of 3 it would require about 0.16 lb/sec of air at a supply pressure of 540 psia. Continuous operation for periods up to 1 hour could be achieved with a farm of 80 compressed air bottles, for example. However, the optimized design would have a throat height of 0.5mm. Therefore pragmatic considerations related to fabrication may dictate a non-optimal design. Reducing the exit Mach number to 2.5, for example, would increase the throat height to 1.0mm with a small (15%) penalty in mass flow rate.« less

Authors:
Publication Date:
Research Org.:
General Applied Science Labs., Inc., Westbury, NY (USA)
OSTI Identifier:
6008340
Report Number(s):
UCRL-15051
DOE Contract Number:  
W-7405-ENG-48
Resource Type:
Technical Report
Country of Publication:
United States
Language:
English
Subject:
43 PARTICLE ACCELERATORS; ACCELERATORS; APERTURES; VACUUM SYSTEMS; SHOCK WAVES; SPECIFICATIONS; SUPERSONIC FLOW; FLUID FLOW; OPENINGS; 430303* - Particle Accelerators- Experimental Facilities & Equipment

Citation Formats

Erdos, J I. Conceptual design and performance estimates for a supersonic aerodynamic window for the ATA vacuum system aperature. Final report. [Advanced Test Accelerator]. United States: N. p., 1979. Web.
Erdos, J I. Conceptual design and performance estimates for a supersonic aerodynamic window for the ATA vacuum system aperature. Final report. [Advanced Test Accelerator]. United States.
Erdos, J I. 1979. "Conceptual design and performance estimates for a supersonic aerodynamic window for the ATA vacuum system aperature. Final report. [Advanced Test Accelerator]". United States.
@article{osti_6008340,
title = {Conceptual design and performance estimates for a supersonic aerodynamic window for the ATA vacuum system aperature. Final report. [Advanced Test Accelerator]},
author = {Erdos, J I},
abstractNote = {A family of supersonic aerodynamic window devices for the ATA aperture have been examined. These included transverse supersonic jet flows of the compression window type, the expansion window type, and an extended expansion window type, as well as an axial supersonic ejector type window. The pure compression type window was rejected because it would require a nozzle exit Mach number exceeding 8.5 to support an attached shock wave. The pure expansion window is optimized at an exit Mach number of unity, but requires 4 times the mass flow rate of the pure compression window, and would probably be unstable at M/sub e/ < 1.5 to 2.0. The extended expansion window was found to require mass flows of the same order as the pure compression window, but is optimized at M/sub e/ approx. = 3. The supersonic ejector would require two stages each having an exit Mach number exceeding 6 to achieve mass flow rates competitive with the extended expansion window. In addition, it appears very doubtful that an efficient ejector could be designed within the overall length limitation. Ejector designs which might meet the length limitation will probably require substantially (2 to 3 times) higher mass flow rates than the extended expansion window. Therefore, the supersonic transverse extended-expansion window (STEW) is considered the preferred design. At an exit Mach number of 3 it would require about 0.16 lb/sec of air at a supply pressure of 540 psia. Continuous operation for periods up to 1 hour could be achieved with a farm of 80 compressed air bottles, for example. However, the optimized design would have a throat height of 0.5mm. Therefore pragmatic considerations related to fabrication may dictate a non-optimal design. Reducing the exit Mach number to 2.5, for example, would increase the throat height to 1.0mm with a small (15%) penalty in mass flow rate.},
doi = {},
url = {https://www.osti.gov/biblio/6008340}, journal = {},
number = ,
volume = ,
place = {United States},
year = {Fri Jun 01 00:00:00 EDT 1979},
month = {Fri Jun 01 00:00:00 EDT 1979}
}

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