Download or read book Flow field Study about a Hemisphere cylinder in the Transonic and Low Supersonic Mach Number Range written by T. Hsieh and published by . This book was released on 1975 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical and experimental study has been conducted of a flow field about a hemisphere-cylinder at zero incidence in the transonic and low supersonic Mach number range (M = 0.7 to 2.0). For M less than or equal to 1, the method used is a combination of the time-dependent solution for the hemispherical nose portion and the method-of-characteristics solution for the cylindrical body portion. The relaxation method has been used for Mach numbers from 0.7 to 1.3. Experimental results indicate a strong interaction of the shock and boundary layer for M approximately equal to 0.8.
Download or read book Flow Field Study about a Hemisphere Cylinder in the Transonic and Low Supersonic Mach Number Range written by and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical and experimental study has been conducted of a flow field about a hemisphere-cylinder at zero incidence in the transonic and low supersonic Mach number range (M = 0.7 to 2.0). For M less than or equal to 1, the method used is a combination of the time-dependent solution for the hemispherical nose portion and the method-of-characteristics solution for the cylindrical body portion. The relaxation method has been used for Mach numbers from 0.7 to 1.3. Experimental results indicate a strong interaction of the shock and boundary layer for M approximately equal to 0.8.
Download or read book Flow Field Study about a Hemisphere Cylinder in the Transonic and Low Supersonic Mach Number Range written by and published by . This book was released on 1975 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: A theoretical and experimental study has been conducted of a flow field about a hemisphere-cylinder at zero incidence in the transonic and low supersonic Mach number range (M = 0.7 to 2.0). For M less than or equal to 1, the method used is a combination of the time-dependent solution for the hemispherical nose portion and the method-of-characteristics solution for the cylindrical body portion. The relaxation method has been used for Mach numbers from 0.7 to 1.3. Experimental results indicate a strong interaction of the shock and boundary layer for M approximately equal to 0.8.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1993 with total page 484 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Annual Index written by and published by . This book was released on 1976 with total page 876 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Computational and Numerical Simulations written by Jan Awrejcewicz and published by BoD – Books on Demand. This book was released on 2014-02-12 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computational and Numerical Simulations is an edited book including 20 chapters. Book handles the recent research devoted to numerical simulations of physical and engineering systems. It presents both new theories and their applications, showing bridge between theoretical investigations and possibility to apply them by engineers of different branches of science. Numerical simulations play a key role in both theoretical and application oriented research.
Download or read book Aerodynamic Characteristics of 2 3 and 4 Caliber Tangent ogive Cylinders with Nose Bluffness Ratios of 0 00 0 25 0 50 and 0 75 at Mach Numbers from 0 6 to 4 0 written by Carroll B. Butler and published by . This book was released on 1977 with total page 248 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report summarizes wind tunnel test data on various body alone configurations which provide a data matrix for bluff and pointed bodies of revolution with systematic variations in nose bluffness, nose fineness ratio, and cylinder afterbody fineness ratio. Modular model components were used to obtain static stability and drag data, with emphasis on the effect of nose bluffness on drag. Although data is included for tangent ogive noses of fineness ratio 2, 2.25, 2.5, 3.0, and 4, the nose fineness ratios of 2, 3, and 4 calibers include a systematic variation in nose bluffness ratios of 0.00, 0.25, 0.50, and 0.75 on cylindrical midsections of 5, 7, 9, and 11 calibers. A 1-caliber cylindrical afterbody is used with all configurations in this report.
Download or read book U S Government Research Reports written by and published by . This book was released on 1964 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Paper written by and published by . This book was released on 1966 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Fourteenth International Conference on Numerical Methods in Fluid Dynamics written by Suresh M. Deshpande and published by Springer. This book was released on 1995-08-18 with total page 728 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computational Fluid Dynamics has now grown into a multidisciplinary activity with considerable industrial applications. The papers in this volume bring out the current status and future trends in CFD very effectively. They cover numerical techniques for solving Euler and Navier-Stokes equations and other models of fluid flow, along with a number of papers on applications. Besides the 88 contributed papers by research workers from all over the world, the book also includes 6 invited lectures from distinguished scientists and engineers.
Download or read book Technical Abstract Bulletin written by and published by . This book was released on with total page 812 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1961 with total page 1096 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 1971 with total page 580 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)
Download or read book Index to NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960-07 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Selected Listing of NASA Scientific and Technical Reports for written by and published by . This book was released on 1960 with total page 450 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Index of NASA Technical Publications written by United States. National Aeronautics and Space Administration and published by . This book was released on 1960 with total page 448 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of Separated Flow about a Hemisphere cylinder at 0 to 19 deg Incidence in the Mach Number Range from 0 6 to 1 5 written by T. Hsieh and published by . This book was released on 1976 with total page 242 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this investigation was to evaluate various jet simulation parameters in an attempt to establish a method of matching hot jet interference with cold jet flows. Successful parameters were determined based on their ability to correlate integrated afterbody pressure drag, a measurement of aerodynamic interference, for jet flows of varying total temperature. Data used in this investigation were obtained from experiments conducted in the AEDC Propulsion Wind Tunnel (16T) with three different isolated nozzle/afterbody configurations at free-stream Mach numbers from 0.6 to 1.5. Gas temperature effects on pressure drag were acquired with a convergent nozzle utilizing an air/ethylene burner to produce gas temperatures from 540 to 3,300 R. In addition, the jet effects of varying internal nozzle geometry, specifically nozzle divergence half-angle and nozzle exit-to-throat area ratio, were investigated utilizing high-pressure air as the nozzle exhaust gas. Jet simulation parameters were evaluated for jet flows where nozzle exit-to-throat area ratio was varied from 1.0 to approximately 1.5 and where divergence half-angle was varied from 0 to 10 deg.
