Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Static Stability And Control Of Canard Configurations At Mach Numbers From 070 To 222 Longitudinal Characteristics Of A Triangular Wing And Unswept Canard
Download Static Stability And Control Of Canard Configurations At Mach Numbers From 070 To 222 Longitudinal Characteristics Of A Triangular Wing And Unswept Canard full books in PDF, epub, and Kindle. Read online Static Stability And Control Of Canard Configurations At Mach Numbers From 070 To 222 Longitudinal Characteristics Of A Triangular Wing And Unswept Canard ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of a Triangular Wing and Unswept Canard by : Victor L. Peterson
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of a Triangular Wing and Unswept Canard written by Victor L. Peterson and published by . This book was released on 1958 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.15 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails by : Victor L. Peterson
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails written by Victor L. Peterson and published by . This book was released on 1961 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of an Unswept Wing and Canard by : Victor L. Peterson
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of an Unswept Wing and Canard written by Victor L. Peterson and published by . This book was released on 1958 with total page 29 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio 3.1 unswept wing, an aspect ratio 3.0 unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.33 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of a Triangular Wing and Canard by : John W. Boyd
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of a Triangular Wing and Canard written by John W. Boyd and published by . This book was released on 1958 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Lateral-directional Characteristics of an Unswept Wing and Canard by : Victor L. Peterson
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Lateral-directional Characteristics of an Unswept Wing and Canard written by Victor L. Peterson and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Stability and Control Characteristics of a Triangular Wing and Canard Configuration at Mach Numbers from 2.58 to 3.53 by : C. Ernest Hedstrom
Download or read book Static Stability and Control Characteristics of a Triangular Wing and Canard Configuration at Mach Numbers from 2.58 to 3.53 written by C. Ernest Hedstrom and published by . This book was released on 1958 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 by : Samuel M. Dollyhigh
Download or read book Static Longitudinal Aerodynamic Characteristics of Close-coupled Wing-canard Configurations at Mach Numbers from 1.60 to 2.86 written by Samuel M. Dollyhigh and published by . This book was released on 1971 with total page 126 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location.
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.7 to 2.22 - Lateral-directional Characteristics of a Triangular Wing and Canard by : Victor L. Peterson
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.7 to 2.22 - Lateral-directional Characteristics of a Triangular Wing and Canard written by Victor L. Peterson and published by . This book was released on 1958 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 by : Victor L. Peterson
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 written by Victor L. Peterson and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: The static aerodynamic characteristics of a canard airplane configuration having twin vertical stabilizing surfaces are presented. The model consisted of a wing and canard both of triangular plan form and aspect ratio 2 mounted on a Sears-Haack body of fineness ratio 12.5 and two swept and tapered wing-mounted vertical tails of aspect ratio 1.35. Data are presented for Mach numbers from 0.70 to 2.22 and for angles of attack from -6 degrees to +18 degrees at 0 degrees and 5 degrees sideslip. Tests were made with the canard off and with the canard on. Nominal canard deflection angles ranged from 0 degrees to 10 degrees. The Reynolds number was 3.68 times 10 to the 6th power based on the wing mean aerodynamic chord. Selected portions of the data obtained in this investigation are compared with previously published results for the same model having a single vertical tail instead of twin vertical tails. (Author).
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Triangular Wing and Canard on an Extended Body by : John W. Boyd
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Triangular Wing and Canard on an Extended Body written by John W. Boyd and published by . This book was released on 1958 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Longitudinal Stability and Control Characteristics at Mach Numbers from 0.70 to 2.22 of a Triangular Wing Configuration Equipped with a Canard Control, a Trailing-edge-flap Control, Or a Cambered Forebody by : John W. Boyd
Download or read book Longitudinal Stability and Control Characteristics at Mach Numbers from 0.70 to 2.22 of a Triangular Wing Configuration Equipped with a Canard Control, a Trailing-edge-flap Control, Or a Cambered Forebody written by John W. Boyd and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Deflected Wing Tips on the Aerodynamic Characteristics of a Canard Configuration at Mach Numbers from 0.7 to 3.5 by : Victor L. Peterson
Download or read book Effects of Deflected Wing Tips on the Aerodynamic Characteristics of a Canard Configuration at Mach Numbers from 0.7 to 3.5 written by Victor L. Peterson and published by . This book was released on 1960 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Stability Characteristics of a Delta-winged Configuration with a Canard Control and Nacelles at Mach Numbers from 0.25 to 3.50 by : LeRoy S. Fletcher
Download or read book Static Stability Characteristics of a Delta-winged Configuration with a Canard Control and Nacelles at Mach Numbers from 0.25 to 3.50 written by LeRoy S. Fletcher and published by . This book was released on 1962 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails by : Victor L. Peterson
Download or read book Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails written by Victor L. Peterson and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Wing Height on the Stability and Control Characteristics at a Mach Number of 2.01 of a Canard Airplane Configuration with a 70 Deg Delta Wing by :
Download or read book Effects of Wing Height on the Stability and Control Characteristics at a Mach Number of 2.01 of a Canard Airplane Configuration with a 70 Deg Delta Wing written by and published by . This book was released on 1960 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Static Longitudinal Characteristics at Mach Numbers Up to 0.95 of a Triangular-wing Canard Model Having a Triangular Control by : Jack D. Stephenson
Download or read book The Static Longitudinal Characteristics at Mach Numbers Up to 0.95 of a Triangular-wing Canard Model Having a Triangular Control written by Jack D. Stephenson and published by . This book was released on 1951 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations by : William C. Steeman
Download or read book Investigation at High Subsonic Speeds of the Static Longitudinal and Lateral Stability Characteristics of Two Canard Airplane Configurations written by William C. Steeman and published by BiblioGov. This book was released on 2013-07 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The present investigation was conducted in the Langley high-speed 7-by 10-foot tunnel to determine the static longitudinal and lateral stability characteristics at high subsonic speeds of two canard airplane configurations previously tested at supersonic speeds. The Mach number range of this investigation extended from 0.60 to 0.94 and a maximum angle-of-attack range of -2dewg to 24deg was obtained at the lowest test Mach number. Two wing plan forms of equal area were studied in the present tests; one was a 60deg delta wing and the other was a trapezoid wing having an aspect ratio of 3, taper ratio of 0.143, and an unswept 80-percent-chord line. The canard control had a trapezoidal plan form and its area was approximately 11.5 percent of the wing area. The model also had a low-aspect-ratio highly swept vertical tail and twin ventral fins. The longitudinal control characteristics of the models were consistent with past experience at low speed on canard configurations in that stalling of the canard surface occurred at moderate and high control deflections for moderate values of angle of attack. This stalling could impose appreciable limitations on the maximum trim-lift coefficient attainable. The control effectiveness and maximum value of trim-lift was significantly increased by addition of a body flap having a conical shape and located slightly behind the canard surface on the bottom of the body. Addition of the canard surface at 0deg deflection had relatively little effect on overall directional stability of the delta-wing configuration; however, deflection of the canard surface from 0deg to 10deg had a large favorable effect on directional stability at high angles of attack for both the trapezoid- and delta-wing configurations.
