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Author : James A. Keenan
Publisher :
ISBN 13 :
Total Pages : 360 pages
Book Rating : 4.:/5 (317 download)
Download or read book The Effects of Winglets on Low Aspect Ratio Wings at Supersonic Mach Numbers written by James A. Keenan and published by . This book was released on 1991 with total page 360 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : James Anthony Keenan
Publisher :
ISBN 13 :
Total Pages : 352 pages
Book Rating : 4.:/5 (31 download)
Download or read book The Effects of Winglets on Low Aspect Ratio Wings at Supersonic Mach Numbers written by James Anthony Keenan and published by . This book was released on 1991 with total page 352 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722370114
Total Pages : 66 pages
Book Rating : 4.3/5 (71 download)
Download or read book Effects of Winglets on the Drag of a Low-Aspect-Ratio Configuration written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation has been performed to determine the effect of winglets on the induced drag of a low-aspect-ratio wing configuration at Mach numbers between 0.30 and 0.85 and a nominal angle-of-attack range from -2 deg to 20 deg. Results of the tests at the cruise lift coefficient showed significant increases in lift-drag ratio for the winglet configuration relative to a wing-alone configuration designed for the same lift coefficient and Mach number. Further, even larger increases in lift-drag ratio were observed at lift coefficients above the design value at all Mach numbers tested. The addition of these winglets had a negligible effect on the static lateral-directional stability characteristics of the configuration. No tests were made to determine the effect of these winglets at supersonic Mach numbers, where increases in drag caused by winglets might be more significant. Computational analyses were also performed for the two configurations studied. Linear and small-disturbance formulations were used. The codes were found to give reasonable performance estimates sufficient for predicting changes of this magnitude. Smith, Leigh Ann and Campbell, Richard L. Langley Research Center...
Author : Edward F. Ulmann
Publisher :
ISBN 13 :
Total Pages : 19 pages
Book Rating : 4.:/5 (11 download)
Download or read book Aerodynamic Characteristics of Low-aspect-ratio Wings at High Supersonic Mach Numbers written by Edward F. Ulmann and published by . This book was released on 1953 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John A. Axelson
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.3/5 (91 download)
Download or read book An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence written by John A. Axelson and published by . This book was released on 1948 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability.
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722836740
Total Pages : 88 pages
Book Rating : 4.8/5 (367 download)
Download or read book Theoretical-Numerical Study of Feasibility of Use of Winglets on Low Aspect Ration Wings at Subsonic and Transonic Mach Numbers to Reduce Drag written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: A numerical design study was conducted to assess the drag reduction potential of winglets installed on a series of low aspect ratio wings at a design point of M=0.8, C sub L=0.3. Wing-winglet and wing-alone design geometries were obtained for wings of aspect ratios between 1.75 and 2.67, having leading edge sweep angles between 45 and 60 deg. Winglet length was fixed at 15% of wing semispan. To assess the relative performance between wing-winglet and wing-alone configurations, the PPW nonlinear extended small disturbance potential flow code was utilized. This model has proven to yield plausible transonic flow field simulations for the series of low aspect ratio configurations selected. Predicted decreases in pressure drag coefficient for the wing-winglet configurations relative to the corresponding wing-alone planform are about 15% at the design point. Predicted decreases in wing-winglet total drag coefficient are about 12%, relative to the corresponding wing-alone design. Longer winglets (25% of the wing semispan) yielded decreases in the pressure drag of up to 22% and total drag of up to 16.4%. These predicted drag coefficient reductions are comparable to reductions already demonstrated by actual winglet designs installed on higher aspect ratio transport type aircraft. Kuhlman, John M. and Liaw, Paul and Cerney, Michael J. Unspecified Center...
Author : Ross B. Robinson
Publisher :
ISBN 13 :
Total Pages : 32 pages
Book Rating : 4.3/5 (91 download)
Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing-body Combinations Having Cambered Wings with an Aspect Ratio of 3.5 and a Taper Ratio of 0.2 written by Ross B. Robinson and published by . This book was released on 1952 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Richard T. Whitcomb
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (31 download)
Download or read book A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios written by Richard T. Whitcomb and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.
Author : Thomas A. Byrdsong
Publisher :
ISBN 13 :
Total Pages : 130 pages
Book Rating : 4.F/5 ( download)
Download or read book Flight Measurements of Lifting Pressures for a Thin Low-aspect-ratio Wing at Subsonic, Transonic, and Low Supersonic Speeds written by Thomas A. Byrdsong and published by . This book was released on 1977 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : John C. Heitmeyer
Publisher :
ISBN 13 :
Total Pages : 20 pages
Book Rating : 4.:/5 (712 download)
Download or read book Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds - Plane Triangular Wing of Aspect Ratio 3 with NACA 0003-63 Section written by John C. Heitmeyer and published by . This book was released on 1951 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wing-body combination having a plane triangular wing of aspect ratio 3 and NACA 0003-63 sections in streamwise planes has been investigated at both subsonic and supersonic Mach numbers. The lift, drag, and pitching moment of the model are presented for Mach numbers from 0.60 to 0.92 and from 1.20 to 1.70 at a Reynolds number of 4.80 million. The variations of the characteristics with Reynolds number are also shown for several Mach numbers.
Author : Lee Winograd
Publisher :
ISBN 13 :
Total Pages : 144 pages
Book Rating : 4.:/5 (29 download)
Download or read book The Longitudinal Stability Derivatives of Low-aspect Ratio Rectangular Wing in Supersonic Flow written by Lee Winograd and published by . This book was released on 1955 with total page 144 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 : Herbert S. Ribner
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.3/5 (91 download)
Download or read book Stability Derivatives of Triangular Wings at Supersonic Speeds written by Herbert S. Ribner and published by . This book was released on 1948 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: The analysis of the stability derivatives of low-aspect-ratio triangular wings at subsonic and supersonic speeds, given in NACA TN No. l423, is extended to apply to triangular wings having large vertex angles and traveling at supersonic speeds. The lift, rolling moment due to siderlip, and damping in roll and pitch for this more general case have been treated elsewhere on the basis of the theory of small disturbances.
Author : Leigh Ann Smith
Publisher :
ISBN 13 :
Total Pages : 66 pages
Book Rating : 4.:/5 (317 download)
Download or read book Effects of Winglets on the Drag of a Low-Aspect-Ratio Configuration written by Leigh Ann Smith and published by . This book was released on 1996 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Donald S. Woolston
Publisher :
ISBN 13 :
Total Pages : 50 pages
Book Rating : 4.:/5 (31 download)
Download or read book Some Divergence Characteristics of Low-aspect-ratio Wings at Transonic and Supersonic Speeds written by Donald S. Woolston and published by . This book was released on 1960 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of chordwise, or camber, divergence at transonic and supersonic speeds is treated with primary emphasis on slender delta wings having a cantilever support at the trailing edge. Experimental and analytical results are presented for four wing models having apex half-angles of 5 deg, 10 deg, 15 deg, and 20 deg. A Mach number range from 0.8 to 7.3 is covered. The analytical results include calculations based on small-aspect-ratio theory, lifting-surface theory, and strip theory. A closed-form solution of the equilibrium equation is given, which is based on low-aspect-ratio theory but which applies only to certain stiffness distributions. Also presented is an iterative procedure for use with other aerodynamic theories and with arbitrary stiffness distribution.
Author : Mitchel H. Bertram
Publisher :
ISBN 13 :
Total Pages : 58 pages
Book Rating : 4.3/5 (91 download)
Download or read book Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-wedge Sections with the Maximum Thickness at 0.18 Chord written by Mitchel H. Bertram and published by . This book was released on 1954 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section has been conducted at the Langley 11-inch hypersonic tunnel. These wings had a maximum thickness of 8 percent of the chord located at the 18-percent-chord point. For the wings tested at a Mach number of 6.9, the semiapex angle was varied from 5 to 30 degrees and the wings were tested over a range of angle of attack from 0 to 28 degrees and Reynolds numbers in the range of 800,000 to 3,600,000 based on root chord. In addition, pertinent results from tests at Mach number as low as 1.62 have been utilized. The shock-expansion theory and the Newtonian impact theory have been used to analyze the effects of changes made in the various parameters investigated.
Author : John A. Moore
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.3/5 (91 download)
Download or read book Experimental Determination of Damping in Pitch of Swept and Delta Wings at Supersonic Mach Numbers written by John A. Moore and published by . This book was released on 1957 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The damping-in-pitch derivative was determined experimentally at Mach numbers of 2.96 and 3.92 for two delta wings having aspect ratios of 2 and 3 and for one sweptback tapered wing having an aspect ratio of 3 by using a free-oscillation technique. The tests were made at Reynolds numbers based on mean aerodynamic chord from 4,000,000 to 12,000,000 for an angle-of-attack range of zero to 10 degrees. The reduced-frequency parameter ranged from 0.006 to 0.022.
