Author: T. W. Tsukahira
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 330
Book Description
Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately . 125 scale model air induction systems. The baseline models included a two- dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers.
Supersonic Inlet Investigation
Author: T. W. Tsukahira
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 330
Book Description
Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately . 125 scale model air induction systems. The baseline models included a two- dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 330
Book Description
Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately . 125 scale model air induction systems. The baseline models included a two- dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers.
Supersonic Inlet Investigation. Volume III. Wind Tunnel Data Report
Author: Tatsuo W. Tsukahira
Publisher:
ISBN:
Category :
Languages : en
Pages : 159
Book Description
Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately .125 scale model air induction systems. The baseline models included a two-dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 159
Book Description
Presented herein are wind tunnel data from an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests using approximately .125 scale model air induction systems. The baseline models included a two-dimensional external compression inlet, a half-axisymmetric external compression inlet, and a two-dimensional mixed compression inlet. Alternate configurations for the external compression baseline inlets were also investigated. Tests were conducted at transonic and supersonic Mach numbers in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a well defined nonuniform flow field, the latter representing partial simulation of a vehicle flow field. Steady state performance data (i.e., pressure recovery, pressure distortion, and turbulence levels) are provided at a simulated compressor face and immediately downstream of the inlet throat for the various inlet configurations tested. Additional diagnostic data are provided in the way of surface pressures and boundary layer pressures on the inlet compression surfaces and in the subsonic diffusers. (Author).
Supersonic Inlet Investigation
Author: Nasim F. Amin
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
Book Description
A one-dimensional mathematical dynamic simulation model for predicting the transient behavior of air induction systems for advanced tactical aircraft operating in the supersonic portion of the flight spectrum is discussed. As a part of the simulation model, control system logic is included to provide control system design criteria necessary to maintain air induction system response to selected input disturbances within prescribed limits. The model is applicable to both external and mixed compression inlets operating at supersonic conditions. The 'lumped parameter' concept is used in simulating the dynamic response of the subsonic duct downstream of the terminal shock, with the duct divided into three lumps.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 366
Book Description
A one-dimensional mathematical dynamic simulation model for predicting the transient behavior of air induction systems for advanced tactical aircraft operating in the supersonic portion of the flight spectrum is discussed. As a part of the simulation model, control system logic is included to provide control system design criteria necessary to maintain air induction system response to selected input disturbances within prescribed limits. The model is applicable to both external and mixed compression inlets operating at supersonic conditions. The 'lumped parameter' concept is used in simulating the dynamic response of the subsonic duct downstream of the terminal shock, with the duct divided into three lumps.
Supersonic Inlet Investigation
Author: T. W. Tsukahira
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 904
Book Description
Reported herein are the results of an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests. The baseline models included a two-dimensional external compression inlet, a two-dimensional mixed compression inlet, and a half-axisymmetric external compression inlet. Alternate configurations for the external compression baseline inlets in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a non-uniform flow field, the later representing partial simulation of a vehicle flow field. Inlet steady state performance was characterized in terms of pressure recovery, pressure distortion, and turbulence levels at a simulated compressor face and immediately downstream of the inlet throat. In addition, detailed analysis and correlation of data obtained with high response dynamic instrumentation were made.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 904
Book Description
Reported herein are the results of an investigation whose primary objective was to develop design criteria and performance tradeoffs for supersonic inlets applicable to advanced tactical aircraft. The objective was accomplished by conducting analysis and wind tunnel tests. The baseline models included a two-dimensional external compression inlet, a two-dimensional mixed compression inlet, and a half-axisymmetric external compression inlet. Alternate configurations for the external compression baseline inlets in the AEDC PWT-4T and VKF-A wind tunnels, respectively. The inlets were tested both isolated and in a non-uniform flow field, the later representing partial simulation of a vehicle flow field. Inlet steady state performance was characterized in terms of pressure recovery, pressure distortion, and turbulence levels at a simulated compressor face and immediately downstream of the inlet throat. In addition, detailed analysis and correlation of data obtained with high response dynamic instrumentation were made.
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 702
Book Description
Technical Abstract Bulletin
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 812
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 812
Book Description
Subject Index to Unclassified ASTIA Documents
Author: Defense Documentation Center (U.S.)
Publisher:
ISBN:
Category : Industrial arts
Languages : en
Pages : 894
Book Description
Publisher:
ISBN:
Category : Industrial arts
Languages : en
Pages : 894
Book Description
Annual Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Keywords Index to U.S. Government Technical Reports
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1160
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1160
Book Description
Keywords Index to U.S. Government Technical Reports (permuted Title Index).
Author: United States. Department of Commerce. Office of Technical Services
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 836
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 836
Book Description