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Author : Ellis Lapin
Publisher :
ISBN 13 :
Total Pages : 150 pages
Book Rating : 4.F/5 ( download)
Download or read book Charts for the Computation of Lift and Drag of Finite Wings at Supersonic Speeds written by Ellis Lapin and published by . This book was released on 1998 with total page 150 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Johns Hopkins University. Applied Physics Laboratory
Publisher :
ISBN 13 :
Total Pages : 102 pages
Book Rating : 4.3/5 (91 download)
Download or read book Handbook of Supersonic Aerodynamics written by Johns Hopkins University. Applied Physics Laboratory and published by . This book was released on 1957 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 656 pages
Book Rating : 4.:/5 (319 download)
Download or read book NASA Technical Note written by and published by . This book was released on 1964 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Edward J. Hopkins
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (31 download)
Download or read book Comparison of Full-scale Lift and Drag Characteristics of the X-15 Airplane with Wind-tunnel Results and Theory written by Edward J. Hopkins and published by . This book was released on 1962 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 18 pages
Book Rating : 4.:/5 (945 download)
Download or read book A Collection and Analysis of Experimental Data on the Aerodynamic Characteristics of Finite Wings : Part I, Lift Curve Slope and Drag Due to Lift of Swept Wings at Supersonic Speeds written by and published by . This book was released on 1954 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Douglas Aircraft Company
Publisher :
ISBN 13 :
Total Pages : 124 pages
Book Rating : 4.E/5 ( download)
Download or read book Reduction of Drag Due to Lift at Supersonic Speeds written by Douglas Aircraft Company and published by . This book was released on 1955 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: $EVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.
Author : Doris Cohen
Publisher : Princeton University Press
ISBN 13 : 1400874947
Total Pages : 251 pages
Book Rating : 4.4/5 (8 download)
Download or read book High Speed Wing Theory written by Doris Cohen and published by Princeton University Press. This book was released on 2015-12-08 with total page 251 pages. Available in PDF, EPUB and Kindle. Book excerpt: Part of the Princeton Aeronautical Paperback series designed to bring to students and research engineers outstanding portions of the twelve-volume High Speed Aerodynamics and Jet Propulsion series. These books have been prepared by direct reproduction of the text from the original series and no attempt has been made to provide introductory material or to eliminate cross reference to other portions of the original volumes. Originally published in 1960. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
ISBN 13 :
Total Pages : 1132 pages
Book Rating : 4.E/5 ( download)
Download or read book Technical Note - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1958 with total page 1132 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Allen F. Donovan
Publisher : Princeton University Press
ISBN 13 : 1400879906
Total Pages : 863 pages
Book Rating : 4.4/5 (8 download)
Download or read book Aerodynamic Components of Aircraft at High Speeds written by Allen F. Donovan and published by Princeton University Press. This book was released on 2015-12-08 with total page 863 pages. Available in PDF, EPUB and Kindle. Book excerpt: Volume VII of the High Speed Aerodynamics and Jet Propulsion series. It deals with applications to specific components of the complete aircraft. Sections of the volume include: aerodynamics of wings at high speed, aerodynamics of bodies at high speed, interaction problems, propellers at high speed, diffusers and nozzles, and nonsteady wing characteristics. Originally published in 1957. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.
Author : Sidney M. Harmon
Publisher :
ISBN 13 :
Total Pages : 34 pages
Book Rating : 4.:/5 (249 download)
Download or read book Calculations of the Supersonic Wave Drag of Nonlifting Wings with Arbitrary Sweepback and Aspect Ratio written by Sidney M. Harmon and published by . This book was released on 1947 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: On the basis of a recently developed theroy for finite sweptback wings at supersonic speeds, calculations of the supersonic wave drag at zero lift were made for a series of wings having thin symmetrical biconvex sections with untapered plan forms and various angles of sweepback and aspect ratios. The results are presented in a unified form so that a single chart permits the direct determnation of the wave drag for this family of airfoils for an extensive range of aspect ratio and sweepback angle for stream Mach numbers up to a value corresponding to that at which the Mach line coincides with the wing leading edge.
Author :
Publisher :
ISBN 13 :
Total Pages : 22 pages
Book Rating : 4.:/5 (317 download)
Download or read book Comparison of Full-scale Lift and Drag Characteristics of the X-15 Airplane with Wind-tunnel Results and Theory written by and published by . This book was released on 1962 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (945 download)
Download or read book A Collection and Analysis of Experimental Data on the Aerodynamic Characteristics of Finite Wings : Part II, Zero Lift Drag of Swept and Straight Wings at Supersonic Speeds written by and published by . This book was released on 1954 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 608 pages
Book Rating : 4.:/5 (31 download)
Download or read book Technical Note written by and published by . This book was released on 1956 with total page 608 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Murray Tobak
Publisher :
ISBN 13 :
Total Pages : 664 pages
Book Rating : 4.F/5 ( download)
Download or read book Dynamic Stability of Vehicles Traversing Ascending Or Descending Paths Through the Atmosphere written by Murray Tobak and published by . This book was released on 1958 with total page 664 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis is given of the oscillatory motions of vehicles which traverse ascending and descending paths through the atmosphere at high speed. The specific case of a skip path is examined in detail, and this leads to a form of solution for the oscillatory motion which should recur over any trajectory. The distinguishing feature of this form is the appearance of the Bessel rather than the trigonometric function as the characteristic mode of oscillation.
Author : E. B. Klunker
Publisher :
ISBN 13 :
Total Pages : 690 pages
Book Rating : 4.F/5 ( download)
Download or read book Effect of a Finite Trailing-edge Thickness on the Drag of Rectangular and Delta Wings at Supersonic Speeds written by E. B. Klunker and published by . This book was released on 1952 with total page 690 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of a finite trailing-edge thickness on the pressure drag of rectangular and delta wings with truncated diamond-shaped airfoil sections with a given thickness ratio is studied for supersonic Mach numbers, linearized theory being used to evaluate the surface pressures. In order to facilitate comparison with wings having sharp trailing edges, the position of maximum thickness and base height are determined for least thickness and base height are determined for least pressure drag as functions of a base-pressure parameter. Comparison is then made between the drag of these wings and similar wings with a sharp trailing edge for various aspect ratios and thickness ratios as a function of stream Mach number. The calculations of the drag characteristics for these wings show that significant drag characteristics for these wings show that significant drag reductions are possible under some condtions at high supersonic speeds. These reductions are relatively independent of aspect ratio for the rectangular wings but depend considerably on aspec ratio for the delta wings; the smaller aspect ratios show the larger drag reductions. Calculations of the spanwise distribution of drag are included to compare further the effect of a base on the drag fro different aspect ratios.
Author : A. J. Eggers (Jr.)
Publisher :
ISBN 13 :
Total Pages : 42 pages
Book Rating : 4.3/5 (126 download)
Download or read book Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds written by A. J. Eggers (Jr.) and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: The problem of designing an aircraft which will develop high lift-drag ratios in flight at high supersonic speeds is attacked using the elementary principle that the components of the aircraft should be individually and collectively arranged to impart the maximum downward and the minimum forward momentum to the surrounding air. This principle in conjunction with other practical considerations of hypersonic flight leads to the study of configurations for which the body is situated entirely below the wing; that is, flat-top wing-body combinations. Theory indicates that sensibly complete aircraft of this type can be designed to develop lift-drag ratios well in excess of 6.
Author : William E. Palmer
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.3/5 (91 download)
Download or read book A Transonic Wind-tunnel Investigation of the Longitudinal Force and Moment Characteristics of Two Delta Wings and One Clipped-tip Delta Wing of 4 Percent Thickness on a Slender Body written by William E. Palmer and published by . This book was released on 1955 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
