Author: Lyndell S. King
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 132
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Book Description
Wind tunnel tests were conducted to determine the flow distribution about fuselage configurations at transonic and supersonic speeds and at angles of attack up to 20 degrees. The models tested were approximately one-twelfth scale and consisted of a main fuselage forebody member and several attachable components. The components were mounted in several combinations to represent different possible configurations for tactical aircraft. Flow distribution surveys were conducted at two inlet locations ahead of and under the wing to assess the effects of forebody geometry for the conditions indicated. The data indicate the influence of the canopy, nose droop, and fuselage shape on flow angularities in the forward survey plane.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 688
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 104
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 896
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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: North Atlantic Treaty Organization. Research and Technology Organization
Publisher:
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 342
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Book Description
Contains the lecture notes prepared for a Special Course on Fluid Dynamics Research on Supersonic Aircraft organized by the RTO Applied Vehicle Technology Panel (AVT). The Course was held at the von Kármán Institute for Fluid Dynamics (VKI) Institute, Rhode-Saint-Genèse, Belgium 25-29 May 1998. The following topics were covered: History & Economics of Supersonic Transports, Supersonic Aerodynamics, Sonic Boom Theory and Minimization, Multi-Point Design Challenges, Vortex Plume Interactions, Propulsion System Design. Presentations on the major world wide supersonic transport programs were also included. The material assembled in this publication was prepared under the combined sponsorship of the RTO Applied Vehicle Technology Panel, the Consultant and Exchange Program of RTO, and the von Kármán Institute (VKI) for Fluid Dynamics.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 16
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 28
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Author: T. W. Tsukahira
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 904
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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.
Author: Robert E. Pendley
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 51
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Book Description
An investigation of three air inlets which were designed for use at transonic speeds was conducted in the Langley 8-foot high-speed tunnel. The basis of the design of these inlets was the use of a nose which was shaped so that substream velocities are maintained on its surface for high-speed operating conditions. Since subsonic velocities would therefore exist on the nose surface up to a limiting supersonic Mach number determined by the nose shape, adverse boundary-layer shock-interaction effects on the nose ahead of the inlet could be avoided at least up to this Mach number.
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1570
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