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An Open Jet Wind Tunnel Investigation Of A Fixed Geometry Diffuser System At Mach Numbers 36 And 70
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Book Synopsis An Open-jet Wind Tunnel Investigation of a Fixed-geometry Diffuser System at Mach Numbers 3.6 and 7.0 by : Richard F. Austin
Download or read book An Open-jet Wind Tunnel Investigation of a Fixed-geometry Diffuser System at Mach Numbers 3.6 and 7.0 written by Richard F. Austin and published by . This book was released on 1966 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: A fixed-geometry second-throat diffuser system was tested in an open-jet wind tunnel at Mach numbers 3.6 and 7.0. These tests were conducted at Reynolds numbers of 1,000,000 and 200,000, based on expansion nozzle exit diameter. The investigation was conducted to provide diffuser design criteria for the AEDC proposed Hypersonic True Temperature Tunnel (Tripltee). At M infinity = 3.6, empty test section diffuser efficiencies of 96% of normal shock recovery were achieved. Under similar conditions at M infinity = 7.0, efficiencies of 90% were obtained, thus establishing that reasonable diffuser efficiencies can be obtained at both Mach numbers with a single diffuser system. Tunnel operation was possible with conical models of up to 18-% blockage, but diffuser efficiency was reduced by 8 to 12%. Tunnel flow could not be established with models in the test section. Models of 8- to 10-% blockage would not permit establishment of tunnel flow at either M infinity = 3.6 or 7.0. It was necessary to inject the models into the flow after the tunnel was started. Limited diffuser heating rate data was obtained at M infinity = 7.0. (Author).
Book Synopsis Subject Index to Unclassified ASTIA Documents by : Defense Documentation Center (U.S.)
Download or read book Subject Index to Unclassified ASTIA Documents written by Defense Documentation Center (U.S.) and published by . This book was released on 1960 with total page 894 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Diffusers, Shrouds, and Mass Injection on the Starting and Operating Characteristics of a Mach 5 Free Jet Tunnel by : John K. Molloy
Download or read book Effect of Diffusers, Shrouds, and Mass Injection on the Starting and Operating Characteristics of a Mach 5 Free Jet Tunnel written by John K. Molloy and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of a Variable-geometry Diffuser on the Operating Characteristics of a Helium Tunnel Designed for a Mach Number in Excess of 20 by : Patrick J. Johnston
Download or read book Effect of a Variable-geometry Diffuser on the Operating Characteristics of a Helium Tunnel Designed for a Mach Number in Excess of 20 written by Patrick J. Johnston and published by . This book was released on 1960 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section by : Rudolf Hermann
Download or read book Diffuser Efficiency and Flow Process of Supersonic Wind Tunnels with Free Jet Test Section written by Rudolf Hermann and published by . This book was released on 1950 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the wind tunnel arrangement under consideration, the air leaves the Laval nozzle as a free jet and is recaptured by the diffuser, which is of the convergent-divergent design. A theoretical analysis of the flow process through this type of supersonic wind tunnel is presented and the diffuser efficiency is calculated for the case of equilibrium between test chamber pressure and pressure in the nozzle exit, assuming one-dimensional, in viscous, steady flow. Using the basic equations of continuity, energy and momentum flux through a bounding surface, an exact solution of the problem is obtained, which is applicable up to Mach number infinite. One of the basic results is, that in the recapturing zone of the diffuser a transition occurs from supersonic to subsonic flow, which is followed by an acceleration in the convergent portion up to sonic velocity at the second throat. The transition is not a normal shock and involves a total pressure loss greater than that of a normal shock at the test section Mach number. A mathematical solution with supersonic velocity after the transition process has no physical existence. A comprehensive comparison of the analytical results with available experiments in supersonic wind tunnels up to Mach number 4.4 regarding diffuser efficiency and second throat area shows good agreement.
Book Synopsis An Investigation of Three-dimensional Wall Interference in a Variable Porosity Transonice Wind Tunnel by : Travis W. Binion (Jr.)
Download or read book An Investigation of Three-dimensional Wall Interference in a Variable Porosity Transonice Wind Tunnel written by Travis W. Binion (Jr.) and published by . This book was released on 1974 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Investigation of Three Axisymmetric Cowls of Different Lengths at Mach Numbers from 0.60 to 0.92 by : Richard J. Re
Download or read book Wind Tunnel Investigation of Three Axisymmetric Cowls of Different Lengths at Mach Numbers from 0.60 to 0.92 written by Richard J. Re and published by . This book was released on 1993 with total page 292 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA SP. written by and published by . This book was released on 1982 with total page 466 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 1966 with total page 1214 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.
Book Synopsis Axisymmetric Hall-arc Jet Wind Tunnel Driver Study by : Robert Richter
Download or read book Axisymmetric Hall-arc Jet Wind Tunnel Driver Study written by Robert Richter and published by . This book was released on 1967 with total page 208 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1982 with total page 634 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722942373 Total Pages :38 pages Book Rating :4.9/5 (423 download)
Book Synopsis Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers from 0. 7 To 1. 4 by : National Aeronautics and Space Administration (NASA)
Download or read book Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers from 0. 7 To 1. 4 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-15 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flush pressure orifices installed on the nose section of a 1/7-scale model of the F-14 airplane were evaluated for use as a flush airdata system (FADS). Wing-tunnel tests were conducted in the 11- by 11-ft Unitary Wind Tunnel at NASA Ames Research Center. A full-scale FADS of the same configuration was previously tested using an F-14 aircraft at the Dryden Flight Research Facility of NASA Ames Research Center (Ames-Dryden). These tests, which were published, are part of a NASA program to assess accuracies of FADS for use on aircraft. The test program also provides data to validate algorithms for the shuttle entry airdata system developed at the NASA Langley Research Center. The wind-tunnel test Mach numbers were 0.73, 0.90, 1.05, 1.20, and 1.39. Angles of attack were varied in 2 deg increments from -4 deg to 20 deg. Sideslip angles were varied in 4 deg increments from -8 deg to 8 deg. Airdata parameters were evaluated for determination of free-stream values of stagnation pressure, static pressure, angle of attack, angle of sideslip, and Mach number. These parameters are, in most cases, the same as the parameters investigated in the flight test program. The basic FADS wind-tunnel data are presented in tabular form. A discussion of the more accurate parameters is included. Larson, Terry J. and Moes, Timothy R. and Siemers, Paul M., III Ames Research Center; Armstrong Flight Research Center; Langley Research Center RTOP 505-60-21...
Book Synopsis An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1.5 to 19.5 by : C. J. Schueler
Download or read book An Investigation of the Model Blockage for Wind Tunnels at Mach Numbers 1.5 to 19.5 written by C. J. Schueler and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the test section flow blockage characteristics was conducted in the 12- by 12 inch supersonic wind tunnel (Tunnel E-1) of the Von Karman Gas Dynamics Facility (AEDC). The purpose of the tests was to determine whether a method of predicting the maximum size model which will permit the establishment of supersonic flow, based on the model frontal area and bow shock-wave strength, is applicable over a wide range of Mach numbers. The tests conducted over the Mach number range from 1.5 to 5 using test models consisting of 15, 20, and 20 degrees half-angle cones, cone-cylinder combinations, and a series of discs. The inadequacy of the one dimensional, normal shock theory for predicting allowable model sizes was reconfirmed in these tests. Furthermore a correlation based on shock wave strength and model frontal area was found to be suitable only over a limited range of Mach numbers. Permissible hemisphere-cylinder model sizes from several wind tunnels covering the Mach number range from 1.5 to 19.5 are also presented.
Book Synopsis Wind-tunnel Investigation of a Flush Airdata System at Mach Numbers from 0.7 to 1.4 by :
Download or read book Wind-tunnel Investigation of a Flush Airdata System at Mach Numbers from 0.7 to 1.4 written by and published by . This book was released on 1990 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of the Performance of the Drive System and Diffuser of the Langley Unitary Plan Wind Tunnel by : Lowell E. Hasel
Download or read book Analysis of the Performance of the Drive System and Diffuser of the Langley Unitary Plan Wind Tunnel written by Lowell E. Hasel and published by . This book was released on 1981 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental and Analytical Investigation of Critical Design Parameters for High Mach Number Open-jet Supersonic Wind Tunnels by : J. D. Lee
Download or read book An Experimental and Analytical Investigation of Critical Design Parameters for High Mach Number Open-jet Supersonic Wind Tunnels written by J. D. Lee and published by . This book was released on 1954 with total page 39 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind Tunnel Investigation of an All Flush Orifice Air Data System for a Large Subsonic Aircraft by : Terry J. Larson
Download or read book Wind Tunnel Investigation of an All Flush Orifice Air Data System for a Large Subsonic Aircraft written by Terry J. Larson and published by . This book was released on 1980 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
