2 edition of study of the sonic-boom characteristics of a blunt body at a Mach number of 4.14 found in the catalog.
study of the sonic-boom characteristics of a blunt body at a Mach number of 4.14
Harry W. Carlson
1977 by National Aeronautics and Space Administration, Scientific and Technical Information Office, for sale by the National Technical Information Service in [Washington], Springfield Va .
Written in English
|Statement||Harry W. Carlson and Robert J. Mack ; NASA Langley Research Center.|
|Series||NASA technical paper ; 1015, NASA technical paper -- 1015.|
|Contributions||Mack, Robert J., Langley Research Center., United States. National Aeronautics and Space Administration.|
|The Physical Object|
|Pagination||, 28,  p. :|
|Number of Pages||28|
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Study of the sonic-boom characteristics of a blunt body at a Mach number of [Washington]: National Aeronautics and Space Administration, Scientific and. Effect of a variable-geometry diffuser on the operating characteristics of a helium tunnel designed for a mach number in excess of 20 / (Washington, [D.C.]: National Aeronautics and Space Administration, ), by Patrick J.
Johnston, Robert D. Witcofski, and Langley Research Center (page images at. Red dotted and black dot-dashed vertical lines denote the critical Mach number for BR = andrespectively.
(a) Total, pressure, and friction drag for BR = and and (b) ratio of. Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them. 1 Texto y sociedad en las letras francesas y francófonas: XVI Coloquio de la Asociación de Profesores de Francés de la Universidad Española (APFUE), celebrado del 25 al 27 de abril de en Lleida.
The book is designed to talk to the reader; in part to be a self-teaching instrument. Learning objectives have been added to each chapter to reflect what is believed to be the most important items to learn from that particular chapter.
mach number aerodynamics compressible flow dimensional vortex finite tunnel. Full text of "NASA scientific and technical publications: A catalog of Special Publications, Reference Publications, Conference Publications, and Technical Papers, " See other formats. Get this from a library. Fundamentals of aerodynamics.
[John D Anderson, Jr.] -- Offering an up-to-date overview of the field of aerodynamics, this edition covers many of the key concepts and topics, such as linearized supersonic flow and oblique shock and expansion waves.
Formulation of the problem of sonic boom by a maneuvering aerofoil as a one-parameter family of Cauchy problems. is the mean of the Mach number m on the nonlinear wavefront just behind. Typical aspect ratios structural of In order to appreciate the effect the planform vary sail- performance high a for 33 from neces- on the aerodynamic characteristics, it is to plane a for to for a jet fighter to which manner in the wing a study sary saucer.
flying Figure illustrates the three. Full text of "Fundamentals Of Aerodynamics, 6th Edition" See other formats. This banner text can have markup. web; books; video; audio; software; images; Toggle navigation.
(a) 著書・雑誌論文 T. Nagata, A. Noguchi, T. Nonomura, K. Ohtani, K. Asai, "Experimental investigation of transonic and supersonic flow over a sphere for Reynolds numbers of 10 5 by free‐flight tests with schlieren visualization", Shock Waves, vol(2), pp ().>>abstract Y.
Uwamino, M. Fujiwara, H. Tomizaki, K. Ohtani, K. Makihara, "Damage of twisted tape tethers. Moreover, virtually every full ray trace sonic boom program in use today is evolved in one way or another from one of these two programs.”20 In Juneat the end of the AST program’s first year, Harry Carlson, Raymond Barger, and Robert Mack of the Langley Research Center published a study on the applicability of sonic boom minimization.
Full text of "Jet Engine Fundamental Of Theory Design Operations" See other formats. Also, wing angle of attack is Q while section angle of attack is differentiated by the use of 01~. The study of section properties allows an objective consideration of the effects of camber, thickness, etc.
The lift characteristics of five illustrative airfoil sections are shown in figure This book emphasizes that the aircraft design process is a science and an art, but also a compromise.
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D CONTENTS. 6 Editorial 10 Angel On A Leash 14 Brace Yourself. Look At 26 A William F. Stifel AKC PRESIDENT By Karl M. Stearns Hereís An Insightful Look At One Of AKCís And. The effects of compressibility at speeds approaching the critical Mach number on the performance of an aircraft are discussed at length in Chapter 11 dealing with high-speed flight.
The basic problem is that, if the air over any part of the aircraft structure (usually the wing) reaches the speed of sound there is an excessive rise in drag. Compare the specific excess power for a 10,lbf TA cruising at the Mach number required for while operating at "Mit" thrust with that for the aircraft cruising at a Mach number of and with that for the aircraft cruising at a Mach number of Nitrogen is often used in wind tunnels as the test gas substitute for air.
The primary purpose of sweepback is to increase the value of the critical Mach number for a given aircraft. The effects of compressibility at speeds approaching the critical Mach number on the performance of an aircraft are discussed at length in Chapter 11 dealing with high-speed flight.
The first f annual report included seven reports. courses capable of application to aeronautics, but only as follows: the Mfassachusetts Institute of Technology an d tlie No. Mach numbers are named after him and are the ratio of the speed of a body or fluid to the local speed of sound, Mach 1 refers to local speed.
When the ‘barrier’ is broken by a flying object (usually an aircraft) it moves from subsonic to supersonic speed and creates a sonic boom. Publishing platform for digital magazines, interactive publications and online catalogs.
Convert documents to beautiful publications and share them worldwide. Title: Computational fluid dynamics, Author: Maximiliano Alegre, Length: pages, Published: Researchers at Langley con-ducted generic and exploratory studies of the stability and control characteristics of this type of configura-tion in several wind tunnels, beginning in with an exploratory conventional static force-test study of variable-sweep version of the X-1 research airplane in the Langley mph 7- by Foot Tunnel In 5/5(2).
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PARD researchers calculated that this vehicle attained a speed of Mach 4_) As Wallops gained experience with its new boosters, the engineers began obtaining valuable data on the flight characteristics of objects moving at re-entry velocities.
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38 The Art of the Helicopter Fig. A body following a circular path is at constant acceleration and if this is calculated, it can be used to derive the forces acting.
(a) shows that after a short time δT, the velocity has changed direction. (b) The rate of change of velocity is the acceleration. Figure Reynolds number/Mach number correlations as a function of velocity and altitude for U.S.
Standard Atmosphere. The corresponding Reynolds number is ( x iO-4 /-too lbf.s2\/ ft4 x ft2 = x i07 CONCEPT OF THE BOUNDARY LAYER For many high-Reynolds-number flows (such as those of interest to the aerodynamicist).
Although the Mach number based on the speed of the complete aircraft may be low, in some cases, significant compressibility effects may be present on components of the vehicle. For example, flow over the upper surface of a wing with a thick high-lift airfoil at high angles of attack may experience Mach numbers approaching 1, even though the.
The Lifting Body Program falls into the category of a low cost, partial technology demonstration to reduce the high technical risk that was emerging from the Dyna Soar program (discussed in Chapter 2).
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