Author: Richard M. Wood
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 104

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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721131433
Category :
Languages : en
Pages : 100

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Book Description
A review of research conducted at the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) into high-speed vortex flows during the 1970s, 1980s, and 1990s is presented. The data are for flat plates, cavities, bodies, missiles, wings, and aircraft with Mach numbers of 1.5 to 4.6. Data are presented to show the types of vortex structures that occur at supersonic speeds and the impact of these flow structures on vehicle performance and control. The data show the presence of both small- and large-scale vortex structures for a variety of vehicles, from missiles to transports. For cavities, the data show very complex multiple vortex structures exist at all combinations of cavity depth to length ratios and Mach number. The data for missiles show the existence of very strong interference effects between body and/or fin vortices. Data are shown that highlight the effect of leading-edge sweep, leading-edge bluntness, wing thickness, location of maximum thickness, and camber on the aerodynamics of and flow over delta wings. Finally, a discussion of a design approach for wings that use vortex flows for improved aerodynamic performance at supersonic speeds is presented. Wood, Richard M. and Wilcox, Floyd J., Jr. and Bauer, Steven X. S. and Allen, Jerry M. Langley Research Center WU 706-51-21-10

Author: Josef Rom
Publisher: Springer Science & Business Media
ISBN: 1461228247
Category : Science
Languages : en
Pages : 408

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Book Description
The aerodynamics of aircraft at high angles of attack is a subject which is being pursued diligently, because the modern agile fighter aircraft and many of the current generation of missiles must perform well at very high incidence, near and beyond stall. However, a comprehensive presentation of the methods and results applicable to the studies of the complex aerodynamics at high angle of attack has not been covered in monographs or textbooks. This book is not the usual textbook in that it goes beyond just presenting the basic theoretical and experimental know-how, since it contains reference material to practical calculation methods and technical and experimental results which can be useful to the practicing aerospace engineers and scientists. It can certainly be used as a text and reference book for graduate courses on subjects related to high angles of attack aerodynamics and for topics related to three-dimensional separation in viscous flow courses. In addition, the book is addressed to the aerodynamicist interested in a comprehensive reference to methods of analysis and computations of high angle of attack flow phenomena and is written for the aerospace scientist and engineer who is familiar with the basic concepts of viscous and inviscid flows and with computational methods used in fluid dynamics.

Author: Richard M. Wood
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 88

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Author: Uwe Ganzer
Publisher:
ISBN:
Category :
Languages : en
Pages : 32

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Book Description
The flow field of the thick delta wing at high subsonic and at supersonic speeds has been the subject of quite a variety of investigations at the Technical University of Berlin. The research work started as early as in the late 60s and is still going on today. It was triggered off by the initiatives of the late 'Dietrich Kuechemann-aiming' at a hypersonic transport and it was taken as a contribution to the Eurohyp activities. The wing configurations investigated at the Technical University of Berlin were of simple shape: Delta wings with straight leading edges and triangular cross sections of different thickness. The interest was focussed on the development of the leeside flow with changes in angle of incidence and main stream Mach number. In addition to that similar delta wings with curved leading edges and also with a jump in leading edge sweep were investigated, as well as two types of wave riders. Besides some theoretical work mainly wind tunnel test were made applying available test techniques: Surface pressure measurements, Pitot measurements in the flow field, flow visualization by Schlieren, vapour and oilfilm technique, skin friction determination using oilfilm interferrogramm and, finally, laser velocimetry (laser-two-focus-system). The experimental investigations were particularly challenging, because of the small models of generally not more than 6 cm span. This limitation arose from the small size of the transonic and supersonic wind tunnel (15 x 15 cm). The paper will give a review on the activities and a brief report on some of the findings.

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 54

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Author: Aga Myung Goodsell
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 48

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Book Description

Author: Gary E. Erickson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 230

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Author: Arthur Wm Rogers
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 91

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Book Description
A theoretical investigation has been made of a general method for predicting the flow field behind the wings of plane and cruciform wings and body combinations at transonic or supersonic speeds and slender configurations at subsonic speeds. The wing trailing-vortex wake is represented initially by line vortices distributed to approximate the spanwise distribution of circulation along the trailing edge of the exposed wing panels. The afterbody is represented by corresponding image vortices within the body. Two-dimensional line-vortex theory is then used to compute the induced velocities at each vortex and the resulting displacement of each vortex is determined by means of a numerical stepwise integration procedure. The method is applied to the calculation of the position of the vortex wake and the estimation of downwash at chsen tail locations behind triangular-wing and cylindrical-body combinations at supersonic speeds. The effects of such geometric parameters as aspect ratio, angle of attack and incidence, ratio of body radius to wing semispan, and angle of bank on the vortex wake behind wings of wing-body combinations were studied. The relative importance of wing vortices, the corresponding image vortices within the body, and body crossflow in determining the total downwash was assessed at a possible tail location.

Author: David S. Miller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 160

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Book Description