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Download or read book Experimental Results for a Hypersonic Nozzle/Afterbody Flow Field, Frank W. Spaid Et Al NASA, Ames Research Center, March 1995 written by and published by . This book was released on with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Frank W. Spaid
Publisher :
ISBN 13 :
Total Pages : 116 pages
Book Rating : 4.:/5 (317 download)
Download or read book Experimental Results for a Hypersonic Nozzle/afterbody Flow Field written by Frank W. Spaid and published by . This book was released on 1995 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781723048968
Total Pages : 116 pages
Book Rating : 4.0/5 (489 download)
Download or read book Experimental Results for a Hypersonic Nozzle/Afterbody Flow Field written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: This study was conducted to experimentally characterize the flow field created by the interaction of a single-expansion ramp-nozzle (SERN) flow with a hypersonic external stream. Data were obtained from a generic nozzle/afterbody model in the 3.5 Foot Hypersonic Wind Tunnel at the NASA Ames Research Center, in a cooperative experimental program involving Ames and McDonnell Douglas Aerospace. The model design and test planning were performed in close cooperation with members of the Ames computational fluid dynamics (CFD) team for the National Aerospace Plane (NASP) program. This paper presents experimental results consisting of oil-flow and shadow graph flow-visualization photographs, afterbody surface-pressure distributions, rake boundary-layer measurements, Preston-tube skin-friction measurements, and flow field surveys with five-hole and thermocouple probes. The probe data consist of impact pressure, flow direction, and total temperature profiles in the interaction flow field. Spaid, Frank W. and Keener, Earl R. and Hui, Frank C. L. Ames Research Center AFTERBODIES; FLOW DISTRIBUTION; FLOW VISUALIZATION; GAS STREAMS; HYPERSONIC FLOW; NOZZLE FLOW; WIND TUNNEL TESTS; COMPUTATIONAL FLUID DYNAMICS; EXHAUST GASES; NATIONAL AEROSPACE PLANE PROGRAM; PRESSURE DISTRIBUTION; SHADOWGRAPH PHOTOGRAPHY; SKIN FRICTION; TEMPERATURE PROFILES...
Author : Frank W. Spaid
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Experimental Results for a Hypersonic Nozzle/afterbody Flow Field written by Frank W. Spaid and published by . This book was released on 1992 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Frank W. Spaid
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (841 download)
Download or read book Experimental Results for a Hypersonic Nozzle written by Frank W. Spaid and published by . This book was released on 1995 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722401399
Total Pages : 64 pages
Book Rating : 4.4/5 (13 download)
Download or read book Flow Analysis and Design Optimization Methods for Nozzle Afterbody of a Hypersonic Vehicle written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report summarizes the methods developed for the aerodynamic analysis and the shape optimization of the nozzle-afterbody section of a hypersonic vehicle. Initially, exhaust gases were assumed to be air. Internal-external flows around a single scramjet module were analyzed by solving the three dimensional Navier-Stokes equations. Then, exhaust gases were simulated by a cold mixture of Freon and Argon. Two different models were used to compute these multispecies flows as they mixed with the hypersonic airflow. Surface and off-surface properties were successfully compared with the experimental data. In the second phase of this project, the Aerodynamic Design Optimization with Sensitivity analysis (ADOS) was developed. Pre and post optimization sensitivity coefficients were derived and used in this quasi-analytical method. These coefficients were also used to predict inexpensively the flow field around a changed shape when the flow field of an unchanged shape was given. Starting with totally arbitrary initial afterbody shapes, independent computations were converged to the same optimum shape, which rendered the maximum axial thrust. Baysal, Oktay Unspecified Center...
Author : John V. Rakich
Publisher :
ISBN 13 :
Total Pages : 60 pages
Book Rating : 4.:/5 (31 download)
Download or read book A Theoretical and Experimental Study of Hypersonic Flow Over Flared Bodies at Incidence written by John V. Rakich and published by . This book was released on 1966 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William F. Hinson
Publisher :
ISBN 13 :
Total Pages : 50 pages
Book Rating : 4.:/5 (31 download)
Download or read book Experimental Investigation of Multiple-jet Liquid Injection Into Hypersonic Flow written by William F. Hinson and published by . This book was released on 1970 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Vernon Van Hise
Publisher :
ISBN 13 :
Total Pages : 24 pages
Book Rating : 4.:/5 (31 download)
Download or read book Analytic Study of Induced Pressure on Long Bodies of Revolution with Varying Nose Bluntness at Hypersonic Speeds written by Vernon Van Hise and published by . This book was released on 1960 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: A systematic study of induced pressures on a series of bodies of revolution with varying nose bluntness has been made by using the method of characteristics for a perfect gas. The fluid mediums investigated were air and helium and the Mach number range was from 5 to 40. A study of representative shock shapes was also made. Flow parameters obtained from the blast-wave analogy gave good correlations of induced pressures and shock shapes. The induced-pressure correlations yielded empirical equations for air and helium which cover the complete range of nose bluntness considered. (Nose fineness ratios varied from 0.4 to 4.) Available experimental results were in good agreement with the characteristics solutions. Properties connected with the concept of hypersonic similitude enabled correlations of the calculations to be made with respect to nose shape, Mach number, and ratio of specific heats.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722830243
Total Pages : 46 pages
Book Rating : 4.8/5 (32 download)
Download or read book Supersonic Investigation of Two Dimensional Hypersonic Exhaust Nozzles written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-12 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the NASA Lewis 10 x 10 ft supersonic Wind Tunnel to determine the performance characteristics of 2D hypersonic exhaust nozzles/afterbodies at low supersonic conditions. Generally, this type of application requires a single expansion ramp nozzle (SERN) that is highly integrated with the airframe of the hypersonic vehicle. At design conditions (hypersonic speeds), the nozzle generally exhibits acceptable performance. At off-design conditions (transonic to mid-supersonic speeds), nozzle performance of a fixed geometry configuration is generally poor. Various 2-D nozzle configurations were tested at off-design conditions from Mach 2.0 to 3.5. Performance data is presented at nozzle pressure ratios from 1 to 35. Jet exhaust was simulated with high-pressure air. To study performance of different geometries, nozzle configurations were varied by interchanging the following model parts: internal upstream contour, expansion ramp, sidewalls, and cowl. Carboni, Jeanne D. and Shyne, Rickey J. and Leavitt, Laurence D. and Taylor, John G. and Lamb, Milton Glenn Research Center; Langley Research Center RTOP 763-01-21...
Author : Wilbur C. Nelson
Publisher : Elsevier
ISBN 13 : 1483223310
Total Pages : 801 pages
Book Rating : 4.4/5 (832 download)
Download or read book The High Temperature Aspects of Hypersonic Flow written by Wilbur C. Nelson and published by Elsevier. This book was released on 2014-12-02 with total page 801 pages. Available in PDF, EPUB and Kindle. Book excerpt: The High Temperature Aspects of Hypersonic Flow is a record of the proceedings of the AGARD-NATO Specialists' Meeting, held at the Technical Centre for Experimental Aerodynamics, Rhode-Saint-Genese, Belgium in April 1962. The book contains the papers presented during the meeting that tackled a broad range of topics in the aspects of hypersonic flow. The subjects covered during the meeting include pressure measurements, interference effects, the use of wind tunnels in aircraft development testing, high temperature gas characteristics, boundary layer research, stability and control and the use of rocket vehicles in flight research. Aerospace engineers and aeronautical engineers will find the book invaluable.
Author : James P. Arrington
Publisher :
ISBN 13 :
Total Pages : 78 pages
Book Rating : 4.:/5 (31 download)
Download or read book Longitudinal Characteristics of Several Configurations at Hypersonic Mach Numbers in Conical and Contoured Nozzles written by James P. Arrington and published by . This book was released on 1964 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Linwood B. Callis
Publisher :
ISBN 13 :
Total Pages : 60 pages
Book Rating : 4.:/5 (31 download)
Download or read book An Analysis of Supersonic Flow Phenomena in Conical Nozzles by a Method of Characteristics written by Linwood B. Callis and published by . This book was released on 1966 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : R. C. Bauer
Publisher :
ISBN 13 :
Total Pages : 62 pages
Book Rating : 4.3/5 (91 download)
Download or read book An Application of the Chapman-Korst Theory to Supersonic Nozzle-afterbody Flows written by R. C. Bauer and published by . This book was released on 1977 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Chapman-Korst-type analysis has been developed for estimating the bulk base flow properties of nozzle-afterbody configurations operating at supersonic speeds. The analysis includes the effects of both initial boundary layers, dissimilar thermodynamic properties of both streams, and a third base bleed gas. The inviscid portions of the jet and external flow are computed by the method of characteristics. The turbulent mixing analysis uses the turbulent kinetic energy method to determine the coefficient in a Prandtl-type eddy viscosity model. The empirical coefficients in the turbulent kinetic energy formulation are those developed for the turbulent mixing of jet flows. A new analytical model of the recompression process has been developed that eliminates the need for an empirical recompression factor to determine the stagnating streamline. The analysis is evaluated by comparing with experimental data for Mach 2.0 flow over a two-dimensional blunt base with hydrogen bleed, a two-dimensional backward-facing step and a hot and a cold rocket nozzle-afterbody configuration. Usually the theoretical base pressure is greater than experimental base pressure, indicating the mixing rate is too small. However, the recompression analysis predicts reasonable values of the recompression factor. (Author).
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781723048074
Total Pages : 152 pages
Book Rating : 4.0/5 (48 download)
Download or read book Experimental Investigation of Nozzle/Plume Aerodynamics at Hypersonic Speeds written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt: The work performed by D. W. Bogdanoff and J.-L. Cambier during the period of 1 Feb. - 31 Oct. 1992 is presented. The following topics are discussed: (1) improvement in the operation of the facility; (2) the wedge model; (3) calibration of the new test section; (4) combustor model; (5) hydrogen fuel system for combustor model; (6) three inch calibration/development tunnel; (7) shock tunnel unsteady flow; (8) pulse detonation wave engine; (9) DCAF flow simulation; (10) high temperature shock layer simulation; and (11) the one dimensional Godunov CFD code. Heinemann, K. and Bogdanoff, David W. and Cambier, Jean-Luc Unspecified Center AERODYNAMICS; COMBUSTION CHAMBERS; COMPUTATIONAL FLUID DYNAMICS; DETONATION WAVES; HYDROGEN FUELS; HYPERSONIC SPEED; SHOCK LAYERS; SHOCK TUNNELS; UNSTEADY FLOW; CALIBRATING; COMPUTERIZED SIMULATION; FUEL SYSTEMS; HIGH TEMPERATURE; TEST CHAMBERS; WEDGES...
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722327156
Total Pages : 24 pages
Book Rating : 4.3/5 (271 download)
Download or read book Issues and Approach to Develop Validated Analysis Tools for Hypersonic Flows written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-05 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Critical issues concerning the modeling of low-density hypervelocity flows where thermochemical nonequilibrium effects are pronounced are discussed. Emphasis is on the development of validated analysis tools. A description of the activity in the Ames Research Center's Aerothermodynamics Branch is also given. Inherent in the process is a strong synergism between ground test and real-gas computational fluid dynamics (CFD). Approaches to develop and/or enhance phenomenological models and incorporate them into computational flow-field simulation codes are discussed. These models have been partially validated with experimental data for flows where the gas temperature is raised (compressive flows). Expanding flows, where temperatures drop, however, exhibit somewhat different behavior. Experimental data for these expanding flow conditions are sparse; reliance must be made on intuition and guidance from computational chemistry to model transport processes under these conditions. Ground-based experimental studies used to provide necessary data for model development and validation are described. Included are the performance characteristics of high-enthalpy flow facilities, such as shock tubes and ballistic ranges. Deiwert, George S. Ames Research Center RTOP 506-40-41...
Author : Harold R. Mead
Publisher :
ISBN 13 :
Total Pages : 80 pages
Book Rating : 4.3/5 (91 download)
Download or read book Theoretical Prediction of Pressures in Hypersonic Flow with Special Reference to Configurations Having Attached Leading-edge Shock written by Harold R. Mead and published by . This book was released on 1962 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of tests which are part of an experimental hypersonic research program designed to support an investigation of new theoretical means for the prediction of pressures on attached-shock configurations at hypersonic speeds. The data obtained include six-component force data at Mach 8 for seven configurations which were previously pressure tested at Mach 5 and 8 under the original program. The force tests were run in tunnel B of the Von Karman Facility of the Arnold Engineering Development Center. The ranges of test variables were: angle of attack, -10 degrees to 20 degrees; angle of yaw, -3 degrees to 15 degrees; Reynolds number per foot, 0.8 and 2.0 x 10(superscript 6). Data were also obtained at a nominal Mach number of 21 for three pressure instrumented configurations tested earilier at Mach 5 and 8 under the original program. The tests were run in tunnel HS-2 of the Von Karman Facility. Pitch data were measured over the angle of attack range -5 degrees to 20 degrees at a Reynolds number per foot of approximately 4X10(superscript 6). Some of the measured pressures are compared with thin-shock-layer thoery, Newtonian pressure formula, equivalent-cone and tangent-wedge approximations with the thin-shock-layer theory being generally superior in appropriate applications.
