Distributed Porous Throat Stability Bypass to Increase the Stable Airflow Range of a Mach 2.5 Inlet with 60 Percent Internal Contraction PDF Download
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Author: Robert Joseph Shaw
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
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Book Description
The results of an experimental investigation to increase the stable airflow operating range of a supersonic, mixed-compression inlet with 60-percent internal contraction are presented. Various distributed-porous, throat stability-bypass entrance configurations were tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of about 25 percent was obtained with the optimum configuration if a constant pressure was maintained in the by-pass plenum. The location of the centerbody bleed region had a decided effect on the overall inlet performance. Limited unstart angle-of-attack data are presented.
Author: Robert Joseph Shaw
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
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Book Description
The results of an experimental investigation to increase the stable airflow operating range of a supersonic, mixed-compression inlet with 60-percent internal contraction are presented. Various distributed-porous, throat stability-bypass entrance configurations were tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of about 25 percent was obtained with the optimum configuration if a constant pressure was maintained in the by-pass plenum. The location of the centerbody bleed region had a decided effect on the overall inlet performance. Limited unstart angle-of-attack data are presented.
Author: Glenn A. Mitchell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 406
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 198
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Book Description
Author: Robert Joseph Shaw
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40
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Book Description
The results of an experimental investigation to increase the stable airflow operating range of a supersonic mixed-compression inlet are presented. A distributed educated throat stability-bypass entrance configuration was tested. In terms of diffuser-exit corrected airflow, a large inlet stable airflow range of about 16.1 percent was obtained if a constant pressure was maintained in the bypass plenum. Limited unstart angle of attack data are presented.
Author: Glenn A. Mitchell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
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Book Description
The throat of a Mach 2.5 inlet with a coldpipe termination was fitted with a stability-bypass system. System variations included several stability bypass entrance configurations. Poppet valves controlled the bypass airflow. The inlet stable airflow range achieved with each configuration was determined for both steady state conditions and internal pulse transients. Results are compared with those obtained without a stability bypass system. Transient results were also obtained for the inlet with a choke point at the diffuser exit and for the inlet with large and small stability bypass plenum volumes. Poppet valves at the stability bypass exit provided the inlet with a stable airflow range of 20 percent or greater at all static and transient conditions.
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1446
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Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1388
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Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1408
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Book Description
Author: Glenn A. Mitchell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 108
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Book Description
