Download or read book On the Design and Testing of a Mach 6 Nozzle for a Shock Reflect Type Hypersonic Shock Tunnel written by F. M. Yu and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Design Fabrication and Calibration of a Mach 6 5 Hypersonic Shock Tunnel Nozzle for Scramjet Testing Applications written by Dean Modroukas and published by . This book was released on 1998 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Flow Phenomena in Starting a Hypersonic Shock Tunnel written by Herbert S. Glick and published by . This book was released on 1955 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Mach 4 and Mach 8 Axisymmetric Nozzles for a Shock Tunnel written by Institute for Computer Applications in Science and Engineering and published by . This book was released on 1991 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Aerospace America written by and published by . This book was released on 1994 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Hypersonic Nozzle Design to Avoid Particle Damage written by Charles E. Wittliff and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1993 with total page 556 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Summary of Instrumentation Development and Aerodynamic Research in a Hypersonic Shock Tunnel written by Charles E. Wittliff and published by . This book was released on 1958 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Advanced Hypersonic Test Facilities written by Frank K. Lu and published by AIAA. This book was released on 2002 with total page 694 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book U S Government Research Reports written by and published by . This book was released on 1962 with total page 154 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Mach 4 and Mach 8 Axisymmetric Nozzles for a Shock Tunnel 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 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The performance of two axisymmetric nozzles which were designed to produce uniform, parallel flow with nominal Mach numbers of 4 and 8 is examined. A free-piston-driven shock tube was used to supply the nozzle with high-temperature, high-pressure test gas. The inviscid design procedure treated the nozzle expansion in two stages. Close to the nozzle throat, the nozzle wall was specified as conical and the gas flow was treated as a quasi-one-dimensional chemically-reacting flow. At the end of the conical expansion, the gas was assumed to be calorically perfect, and a contoured wall was designed (using method of characteristics) to convert the source flow into a uniform and parallel flow at the end of the nozzle. Performance was assessed by measuring Pitot pressures across the exit plane of the nozzles and, over the range of operating conditions examined, the nozzles produced satisfactory test flows. However, there were flow disturbances in the Mach 8 nozzle flow that persisted for significant times after flow initiation. Jacobs, P. A. and Stalker, R. J. Langley Research Center NAS1-18605; RTOP 505-90-52-01...
Download or read book The Finding Guide to AIAA Meeting Papers written by American Institute of Aeronautics and Astronautics. Technical Information Service and published by . This book was released on 1996 with total page 184 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Optical Study of the Flow in a Mach 6 Nozzle written by Lynwood H. Luebke and published by . This book was released on 1974 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A qualitative experimental study was performed to visualize the flow in a Pratt and Whitney contoured minimum length gas dynamic laser nozzle. The study was done on a blowdown wind tunnel and the test section was designed to model a single channel of flow in the gas dynamic laser. The nozzle has an area ratio of 66 and accelerates the flow to a Mach number of 6 allowing for boundary layer effects. Dry air or nitrogen at 80F total temperature was used as the flowing media. Total pressure was varied from 90 to 180 psig. The flow was visualized using schlieren optical techniques. Neither separation nor disturbances caused by wakes or shock waves was observed in the divergent section of the nozzle. It was determined that the nozzle performed as designed. Using schlieren photographs, it was determined that the nozzle accelerated the flow to Mach 6. The nozzle did follow ideal gas flow characteristics even though it had a throat height of 0.0058 in. Nozzle throat shocks observed in previous studies and thought to be induced by a non-uniform boundary layer growth in the throat region were not observed in this study.
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:
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1998 with total page 920 pages. Available in PDF, EPUB and Kindle. Book excerpt:
