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:

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:

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:

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:

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...

Download or read book Fluid Flow Analysis of a Hot core Hypersonic wind tunnel Nozzle Concept written by John B. Anders and published by . This book was released on 1972 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A hypersonic-wind-tunnel nozzle concept which incorporates a hot-core flow surrounded by an annular flow of cold air offers a promising technique for maximizing the model size while minimizing the power required to heat the test core. This capability becomes especially important when providing the true-temperature duplication needed for hypersonic propulsion testing. Several two-dimensional wind-tunnel nozzle configurations that are designed according to this concept are analyzed by using recently developed analytical techniques for prediction of the boundary-layer growth and the mixing between the hot and cold coaxial supersonic airflows. The analyses indicate that introduction of the cold annular flow near the throat results in an unacceptable test core for the nozzle size and stagnation conditions considered because of both mixing and condensation effects. Use of a half-nozzle with a ramp on the flat portion does not appear promising because of the thick boundary layer associated with the extra length. However, the analyses indicate that if the cold annular flow is introduced at the exit of a full two-dimensional nozzle, an acceptable test core will be produced. Predictions of the mixing between the hot and cold supersonic streams for this configuration show that mixing effects from the cold flow do not appreciably penetrate into the hot core for the large downstream distances of interest.

Download or read book Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles Including Boundary Layer Turbulence and Real Gas Effects written by Ralph C. Tolle and published by . This book was released on 1996 with total page 274 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Method for Calculating Turbulent Boundary Layer Development in Supersonic and Hypersonic Nozzles Including the Effects of Heat Transfer written by JEROME. PERSH and published by . This book was released on 1956 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Methods of Hypersonics written by J. Lukasiewicz and published by New York : M. Dekker. This book was released on 1973 with total page 366 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Modification of a Three dimensional Supersonic Nozzle Analysis and Comparison with Experimental Data written by Allan R. Bishop and published by . This book was released on 1974 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer program previously developed to analyze three-dimensional supersonic nozzles by the method of characteristics has been modified to study less restrictive nozzle geometries and nonuniform inlet conditions. An example indicates that a one-dimensional calculation that uses an averaged initial profile may be significantly in error. A comparison between the analysis and the data from a three-dimensional experiment shows generally good agreement between the two.

Download or read book A Boundary Layer Study on Hypersonic Nozzles written by Paul Joseph Shall (Jr) and published by . This book was released on 1968 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was made to determine the structure and integrated properties of turbulent boundary layers in hypersonic nozzles, at Mach numbers between 10 and 12. It is concluded that the 1/7-power velocity profile does not agree with the experimental data in this Mach number range. However, a velocity profile based on the Crocco energy relations agrees well with the data as does the corresponding temperature profile, except at the point of maximum temperature. The semi-empirical relationships for boundary layer thickness and displacement thickness, proposed by Burke are strongly supported by the experimental data of this study. (Author).

Download or read book Comparison of Prediction Methods and Studies of Relaxation in Hypersonic Turbulent Nozzle wall Boundary Layers written by Dennis M. Bushnell and published by . This book was released on 1969 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent boundary layer measurements on axisymmetric hypersonic nozzle walls.

Download or read book NOL Hypersonic Tunnel No 4 Results 5 written by P. Wegener and published by . This book was released on 1955 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

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:

Download or read book Theoretical and Experimental Investigation of Boundary Layers in Low Density Hypersonic Axisymmetric Nozzles written by David L. Whitfield and published by . This book was released on 1968 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: The viscous flow region in low density hypersonic axisymmetric nozzles was investigated both theoretically and experimentally. Nonsimilar solutions were obtained for the internal laminar boundary layer equations which include second-order transverse curvature terms. These solutions were obtained on a CDC 1604 digital computer. Four existing low density axisymmetric nozzles were considered. Numerical solutions were obtained for these nozzles using various plenum chamber conditions and wall temperature distributions. The plenum chamber conditions used in the numerical solutions for these nozzles produced a test section Mach number range of about 3.0 to 18.0 and a test section Reynolds number per foot range of about 1000 to 15,000. Some results of the numerical solutions are compared with experimental measurements of pitot pressure, relative heat flux, and nozzle wall heat transfer coefficients. In all comparisons the numerical solutions appear to be consistent with the experimental data. (Author).

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Study of Equilibrium Real gas Effects in Hypersonic Air Nozzles Including Charts of Thermodynamic Properties for Equilibrium Air written by Wayne Douglas Erickson and published by . This book was released on 1960 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt: