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Low Speed Performance Of An Axisymmetric Mixed Compression Supersonic Inlet With Auxiliary Inlets
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Book Synopsis Low-speed Performance of an Axisymmetric, Mixed-compression, Supersonic Inlet with Auxiliary Inlets by : Charles J. Trefny
Download or read book Low-speed Performance of an Axisymmetric, Mixed-compression, Supersonic Inlet with Auxiliary Inlets written by Charles J. Trefny and published by . This book was released on 1986 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Low-speed Performance of an Axisymmetric, Mixed-compression, Supersonic Inlet with Auxiliary Inlets by : Charles J. Trefny
Download or read book Low-speed Performance of an Axisymmetric, Mixed-compression, Supersonic Inlet with Auxiliary Inlets written by Charles J. Trefny and published by . This book was released on 1986 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Technical Paper by : United States. National Aeronautics and Space Administration
Download or read book NASA Technical Paper written by United States. National Aeronautics and Space Administration and published by . This book was released on 1977 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analytic and Experimental Performance of Two Isentropic Mixed Compression Axisymmetric Inlets at Mach Numbers 0.8 to 2.65 by : Donald B. Smeltzer
Download or read book Analytic and Experimental Performance of Two Isentropic Mixed Compression Axisymmetric Inlets at Mach Numbers 0.8 to 2.65 written by Donald B. Smeltzer and published by . This book was released on 1973 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A mixed compression axisymmetric inlet model with a capture diameter of 50 cm was tested at Mach numbers ranging from 0.8 to 2.65 at 0 deg angle of attack and a constant total pressure of approximately 1 atm. Analytical methods accounting for the effects of both viscous and inviscid flows and incorporating empirical bleed discharge coefficients were used in the procedure for designing the inlet contours and the bleed system. Experimental results are compared with analytic predictions and are also compared with results from earlier tests of an inlet with the same internal contours but with a bleed system developed by cut and try methods in the wind tunnel. With the bleed configuration predicted by the design procedure, maximum total pressure recovery at the engine face at the design Mach number of 2.65 was 93 percent, with a total pressure distortion less than 10 percent. Corresponding bleed mass flow was approximately 7.5 percent, which was about 1.3 percent less than predicted. At lower supersonic Mach numbers, pressure recovery and bleed were generally lower and distortion generally higher.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1991 with total page 1460 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1980 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Government Reports Announcements & Index by :
Download or read book Government Reports Announcements & Index written by and published by . This book was released on 1986-08 with total page 1142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NASA Scientific and Technical Publications by :
Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1987 with total page 410 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781719390408 Total Pages :26 pages Book Rating :4.3/5 (94 download)
Book Synopsis Design and Analysis Tool for External-Compression Supersonic Inlets by : National Aeronautics and Space Administration (NASA)
Download or read book Design and Analysis Tool for External-Compression Supersonic Inlets written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-22 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational tool named SUPIN has been developed to design and analyze external-compression supersonic inlets for aircraft at cruise speeds from Mach 1.6 to 2.0. The inlet types available include the axisymmetric outward-turning, two-dimensional single-duct, two-dimensional bifurcated-duct, and streamline-traced Busemann inlets. The aerodynamic performance is characterized by the flow rates, total pressure recovery, and drag. The inlet flowfield is divided into parts to provide a framework for the geometry and aerodynamic modeling and the parts are defined in terms of geometric factors. The low-fidelity aerodynamic analysis and design methods are based on analytic, empirical, and numerical methods which provide for quick analysis. SUPIN provides inlet geometry in the form of coordinates and surface grids useable by grid generation methods for higher-fidelity computational fluid dynamics (CFD) analysis. SUPIN is demonstrated through a series of design studies and CFD analyses were performed to verify some of the analysis results. Slater, John W. Glenn Research Center COMPUTATIONAL FLUID DYNAMICS; SUPERSONIC INLETS; FLOW DISTRIBUTION; AERODYNAMIC CHARACTERISTICS; DRAG; FLOW VELOCITY; SUPERSONIC SPEED; DUCTS; PRESSURE RECOVERY; DESIGN ANALYSIS
Book Synopsis A Supersonic Inlet-engine Control Using Engine Speed as a Primary Variable for Controlling Normal Shock Position by : Francis J. Paulovich
Download or read book A Supersonic Inlet-engine Control Using Engine Speed as a Primary Variable for Controlling Normal Shock Position written by Francis J. Paulovich and published by . This book was released on 1971 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A cross-coupled inlet-engine control system concept is presented for a supersonic propulsion system consisting of a mixed- compression inlet and a turbojet engine. The control system employs manipulation of both bypass door flow area and engine speed to stabilize normal shock position in the inlet. Specifically, the case of slow-acting bypass doors used as a reset control where engine speed is the primary means of shock position control is described. Experimental results are presented showing performance of the control system with a NASA-designed inlet and a turbojet engine operating at Mach 2.5 in the Lewis 10- by 10-Foot Supersonic Wind Tunnel.
Book Synopsis Performance Summary of a Two-dimensional and an Axisymmetric Supersonic Inlet System by :
Download or read book Performance Summary of a Two-dimensional and an Axisymmetric Supersonic Inlet System written by and published by . This book was released on 1966 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book ASME Technical Papers written by and published by . This book was released on with total page 510 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Inlet Investigation by : T. W. Tsukahira
Download or read book Supersonic Inlet Investigation written by T. W. Tsukahira and published by . This book was released on 1971 with total page 904 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis NASA Scientific and Technical Publications by :
Download or read book NASA Scientific and Technical Publications written by and published by . This book was released on 1987 with total page 396 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Bibliography on Aerodynamics of Airframe/engine Integration of High-speed Turbine-powered Aircraft by : Mark R. Nichols
Download or read book Bibliography on Aerodynamics of Airframe/engine Integration of High-speed Turbine-powered Aircraft written by Mark R. Nichols and published by . This book was released on 1980 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Bibliography on Aerodynamics of Airframe/engine Integration of High-speed Turbine-powered Aircraft, Volume 1 by :
Download or read book Bibliography on Aerodynamics of Airframe/engine Integration of High-speed Turbine-powered Aircraft, Volume 1 written by and published by . This book was released on 1980 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Interactive, Design and Educational Tool for Supersonic External-compression Inlets by : Thomas J. Benson
Download or read book An Interactive, Design and Educational Tool for Supersonic External-compression Inlets written by Thomas J. Benson and published by . This book was released on 1994 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
