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Author : M.R. Fink
Publisher :
ISBN 13 :
Total Pages : 6 pages
Book Rating : 4.:/5 (11 download)
Download or read book Axisymmetric Nose Inlet Effects on Supersonic Missile Airloads written by M.R. Fink and published by . This book was released on 1982 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Clyde Hayes
Publisher :
ISBN 13 :
Total Pages : 284 pages
Book Rating : 4.:/5 (317 download)
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations. 1: Axisymmetric Inlets at Supersonic Speeds written by Clyde Hayes and published by . This book was released on 1983 with total page 284 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Clyde Hayes
Publisher :
ISBN 13 :
Total Pages : 404 pages
Book Rating : 4.:/5 (31 download)
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations: Axisymmetric inlets at supersonic speeds written by Clyde Hayes and published by . This book was released on 1983 with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 700 pages
Book Rating : 4.0/5 ( download)
Download or read book A Collection of Technical Papers written by and published by . This book was released on 1982 with total page 700 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Clyde Hayes
Publisher :
ISBN 13 :
Total Pages : 372 pages
Book Rating : 4.:/5 (31 download)
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations: Axisymmetric and two-dimensional inlets at subsonic-transonic speeds written by Clyde Hayes and published by . This book was released on 1983 with total page 372 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Clyde Hayes
Publisher :
ISBN 13 :
Total Pages : 404 pages
Book Rating : 4.:/5 (317 download)
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations. 2: Two-dimensional Inlets at Supersonic Speeds written by Clyde Hayes and published by . This book was released on 1983 with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 376 pages
Book Rating : 4.:/5 (317 download)
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations. 3: Axisymmetric and Two-dimensional Inlets at Subsonic-transonic Speeds written by and published by . This book was released on 1983 with total page 376 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Clyde Hayes
Publisher :
ISBN 13 :
Total Pages : 359 pages
Book Rating : 4.:/5 (11 download)
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations written by Clyde Hayes and published by . This book was released on 1983 with total page 359 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.:/5 (317 download)
Download or read book High Angle of Incidence Implications Upon Air Intake Design and Location for Supersonic Cruise Aircraft and Highly Maneuverable Transonic Aircraft written by and published by . This book was released on 1978 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 696 pages
Book Rating : 4.F/5 ( download)
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1991 with total page 696 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : V. B. Jaware
Publisher :
ISBN 13 : 9788088629955
Total Pages : 0 pages
Book Rating : 4.6/5 (299 download)
Download or read book Effect of Nose Bluntness Intake Features on Hypersonic Inlet Flow Field written by V. B. Jaware and published by . This book was released on 2023-02-11 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of nose bluntness intake features on hypersonic inlet flow field is an important area of research for the design and optimization of hypersonic aircraft. Hypersonic aircraft operate at extremely high speeds, and the design of the intake features can have a significant impact on the performance of the aircraft. The nose bluntness of the intake features can affect the flow field characteristics, which can in turn impact the performance of the engine and the aircraft as a whole. The research on the effect of nose bluntness intake features on hypersonic inlet flow field involves the use of computational fluid dynamics (CFD) simulations to study the flow characteristics of the inlet features. The simulations take into account the geometry and the operational conditions of the inlet features to evaluate their performance. The results of the simulations can be used to optimize the design of the inlet features and improve the performance of the aircraft. The effect of nose bluntness intake features on hypersonic inlet flow field is an important area of research that has significant implications for the design of hypersonic aircraft. By understanding the flow characteristics of the inlet features, researchers can optimize the design to improve the performance of the aircraft. This can lead to increased efficiency, reduced fuel consumption, and improved safety, which are all important considerations in the design of hypersonic aircraft.
Author : Jack D. Coats
Publisher :
ISBN 13 :
Total Pages : 64 pages
Book Rating : 4.3/5 (91 download)
Download or read book Investigation of the Effects of Nose Bluntness on Natural and Induced Boundary-layer Transition on Axisymmetric Bodies in Supersonic Flow written by Jack D. Coats and published by . This book was released on 1973 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: A series of tests has been conducted at free-stream Mach numbers four and eight to determine the effectiveness of three-dimensional boundary-layer trips in promoting transition on very blunt axisymmetric bodies with near equilibrium wall temperatures. Temperature distributions obtained with temperature sensing gages inserted in the model surface were used to locate boundary-layer transition at Mach number four, and qualitative results, based on pitot pressure measurements, were obtained at Mach number eight. A simple modification of a technique proposed by van Driest and Blummer for determining an effective trip size for blunt bodies is shown to yield a correlation applicable to their data on a sphere at Mach number two and the present configurations at Mach number four.
Author :
Publisher :
ISBN 13 :
Total Pages : 654 pages
Book Rating : 4.:/5 (319 download)
Download or read book NASA SP. written by and published by . This book was released on 1992 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Brian Tyler Brooker
Publisher :
ISBN 13 :
Total Pages : 84 pages
Book Rating : 4.:/5 (94 download)
Download or read book Experimental Study on the Effects of Nose Geometry on Drag Over Axisymmetric Bodies in Supersonic Flow written by Brian Tyler Brooker and published by . This book was released on 2014 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new nose shape that was determined using the penetration mechanics to have the least penetration drag has been tested in the supersonic wind tunnel of the University of Alabama to determine the aerodynamic characteristics of this nose shape. The aerodynamic drag measured on the new nose shape and on four additional nose shapes are compared to each other. The results show that the new nose shape has the least aerodynamic drag. The measurements were made at Mach numbers ranging from 1.85 to 3.1. This study also required the maintenance of several components of the University of Alabama's 6-inch by 6-inch supersonic wind tunnel and modification of the existing data acquisition programs. These repairs and modifications included the repair and recalibration of the supersonic wind tunnel, repair of the four component force balance, and the modification of the tunnel's control program.
Author :
Publisher :
ISBN 13 :
Total Pages : 1370 pages
Book Rating : 4.:/5 (31 download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1981 with total page 1370 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.
Author : American Institute of Aeronautics and Astronautics. Technical Information Service
Publisher :
ISBN 13 :
Total Pages : 764 pages
Book Rating : 4.3/5 (91 download)
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 1981 with total page 764 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Yan Kergaravat
Publisher :
ISBN 13 :
Total Pages : 12 pages
Book Rating : 4.:/5 (228 download)
Download or read book Inlet/Body Integration Preliminary Design for Supersonic Air-Breathing Missiles Using Automated Multi-Discilinary Optimization written by Yan Kergaravat and published by . This book was released on 2000 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: In order to reduce the design cycle time and cost and to improve the multi-disciplinary interactions at the preliminary design stage of supersonic air-breathing missiles, an automated optimization method has been developed for inlet/body integration in a concurrent engineering environment. Three disciplines of higher relevance have been considered for the shape optimization problem: propulsion, aerodynamics and electromagnetics. This paper describes the numerical method, which incorporates a genetic algorithm and three analysis modules into the optimization loop. The parametric model of the generic missile is presented. The optimization problem is defined and solved for a given mission and set of specifications. The problem is addressed in three phases corresponding to an increasing number of concurrent disciplines. This progression enables to emphasize the conflicting goals between the disciplines and to understand how the optimizer yields the best compromises. This preliminary study shows interesting results and strong potential for future development and industrial applications.
