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Transonic Wind Tunnel Investigation Of The Effect Of A Horizontal Tail On Longitudinal Stability Of Two 60 Degree Sweptback Wing Body Configurations With Aspect Ratios Of 267 And 400
Download Transonic Wind Tunnel Investigation Of The Effect Of A Horizontal Tail On Longitudinal Stability Of Two 60 Degree Sweptback Wing Body Configurations With Aspect Ratios Of 267 And 400 full books in PDF, epub, and Kindle. Read online Transonic Wind Tunnel Investigation Of The Effect Of A Horizontal Tail On Longitudinal Stability Of Two 60 Degree Sweptback Wing Body Configurations With Aspect Ratios Of 267 And 400 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Transonic Wind-tunnel Investigation of the Effect of a Horizontal Tail on Longitudinal Stability of Two 60 Degree Sweptback-wing-body Configurations with Aspect Ratios of 2.67 and 4.00 by : Joseph D. Brooks
Download or read book Transonic Wind-tunnel Investigation of the Effect of a Horizontal Tail on Longitudinal Stability of Two 60 Degree Sweptback-wing-body Configurations with Aspect Ratios of 2.67 and 4.00 written by Joseph D. Brooks and published by . This book was released on 1958 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation of the Effects of Various Dorsal-fin and Vertical-tail Configurations on the Directional Stability of a Streamlined Body at Transonic Speeds, Transonic-bump Method by : Harold S. Johnson
Download or read book Wind-tunnel Investigation of the Effects of Various Dorsal-fin and Vertical-tail Configurations on the Directional Stability of a Streamlined Body at Transonic Speeds, Transonic-bump Method written by Harold S. Johnson and published by . This book was released on 1953 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Transonic Wind-tunnel Investigation of Aerodynamic-loading Characteristics of a 2-percent-thick Trapezoidal Wing in Combination with Basic and Indented Bodies by : Thomas C. Kelly
Download or read book Transonic Wind-tunnel Investigation of Aerodynamic-loading Characteristics of a 2-percent-thick Trapezoidal Wing in Combination with Basic and Indented Bodies written by Thomas C. Kelly and published by . This book was released on 1957 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.
Book Synopsis Wind Tunnel Investigation of Effect of Yaw on Lateral-stability Characteristics by : Isidore G. Recant
Download or read book Wind Tunnel Investigation of Effect of Yaw on Lateral-stability Characteristics written by Isidore G. Recant and published by . This book was released on 1942 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.
Book Synopsis An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence by : John A. Axelson
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.
Book Synopsis Wind-tunnel Investigation to Determine the Horizontal- and Vertical-tail Contributions to the Static Lateral Stability Characteristics of a Complete-model Swept-wing Configuration at High Subsonic Speeds by : James W. Wiggins
Download or read book Wind-tunnel Investigation to Determine the Horizontal- and Vertical-tail Contributions to the Static Lateral Stability Characteristics of a Complete-model Swept-wing Configuration at High Subsonic Speeds written by James W. Wiggins and published by . This book was released on 1956 with total page 692 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. The results indicate that, in a general, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.
Book Synopsis A Transonic Wind-tunnel Investigation of the Effects of Longitudinal Wing Location and Varying Body Size on the Interference Characteristics of a 45 Degree Sweptback Wing by : Doanld L. Loving
Download or read book A Transonic Wind-tunnel Investigation of the Effects of Longitudinal Wing Location and Varying Body Size on the Interference Characteristics of a 45 Degree Sweptback Wing written by Doanld L. Loving and published by . This book was released on 1953 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Summary of Results of a Wind-tunnel Investigation of Nine Related Horizontal Tails by : Jules B. Dods
Download or read book Summary of Results of a Wind-tunnel Investigation of Nine Related Horizontal Tails written by Jules B. Dods and published by . This book was released on 1955 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a wind-tunnel investigation of a series of models of nine related horizontal tails have been summarized to provide basic design information; to indicate the effects of aspect ratio, sweepback, and changes in the Mach number; and to provide experimental values of the lift and hinge-moment parameters for comparison with values computed by a method employing lifting-surface theory. The models had aspect ratios from 2 to 6, angles of sweepback of the quarter-chord line from 5.7 degrees to 45 degrees, a taper ratio of 0.5, and had 30-percent-chord, sealed, plain flaps. The Mach number was varied from 0.12 to 0.94 for Reynolds numbers of 2, 3, or 4 million. Also, a constant-chord airfoil having the NACA 64A010 section and completely spanning the wind tunnel was tested at a Mach number of 0.12. This airfoil had the same section and flap-chord ratio as the nine horizontal-tail models.
Book Synopsis Wind-tunnel Investigation of the Effects of Horizontal-tail Position on the Low-speed Longitudinal Stability Characteristics of an Airplane Model with a 35 Degrees Sweptback Wing Equipped with Chordwise Fences by : M.J. Queijo
Download or read book Wind-tunnel Investigation of the Effects of Horizontal-tail Position on the Low-speed Longitudinal Stability Characteristics of an Airplane Model with a 35 Degrees Sweptback Wing Equipped with Chordwise Fences written by M.J. Queijo and published by . This book was released on 1951 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Some Lessons Learned with Wind Tunnels by :
Download or read book Some Lessons Learned with Wind Tunnels written by and published by . This book was released on 1986 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Summary and Analysis of Horizontal-tail Contribution to Longitudinal Stability of Swept-wing Airplanes at Low Speeds by : Robert H. Neely
Download or read book Summary and Analysis of Horizontal-tail Contribution to Longitudinal Stability of Swept-wing Airplanes at Low Speeds written by Robert H. Neely and published by . This book was released on 1959 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tail locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 105 and at Mach numbers less than 0.25.
Book Synopsis Combined Effects of Wing Taper and Low Horizontal-tail Position on Longitudinal Stability of a 45 Degree Sweptback Wing-body Combination at Transonic Speeds by : Stanley H. Spooner
Download or read book Combined Effects of Wing Taper and Low Horizontal-tail Position on Longitudinal Stability of a 45 Degree Sweptback Wing-body Combination at Transonic Speeds written by Stanley H. Spooner and published by . This book was released on 1956 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The combined effects of wing taper ratio and low horizontal-tail position on the static longitudinal stability of a 45 degree sweptback wing-body combination with an aspect ratio of approximately 4 have been investigated for a range of Mach numbers from 0.8 to 1.2 in the Langley 8-foot transonic pressure tunnel.
Book Synopsis Wind-tunnel Investigation of the High-subsonic Static Longitudinal Stability Characteristics of Several Wing-body Configurations Designed for High Lift-drag Ratios at a Mach Number of 1.4 by : Paul G. Fournier
Download or read book Wind-tunnel Investigation of the High-subsonic Static Longitudinal Stability Characteristics of Several Wing-body Configurations Designed for High Lift-drag Ratios at a Mach Number of 1.4 written by Paul G. Fournier and published by . This book was released on 1958 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel to investigate the high-subsonic static longitudinal stability characteristics and lift-drag ratios of several wing-body models designed to provide high lift-drag ratios at a Mach number of 1.4. The basic configuration had a thin highly swept wing of aspect ratio 2.91 with NACA 65A-series airfoil sections. Other configurations included bodies modified by two types of indentation and two other wings, one wing without camber but with 4 degrees linear twist (washout) and a second wing with both camber and twist.
Book Synopsis Transonic Wind-tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing-body Combination of Aspect Ratio 4 and Taper Ratio 0.6 by : Robert J. Platt
Download or read book Transonic Wind-tunnel Investigation of the Effects of Sweepback and Thickness Ratio on the Wing Loads of a Wing-body Combination of Aspect Ratio 4 and Taper Ratio 0.6 written by Robert J. Platt and published by . This book was released on 1955 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A transonic investigation of the effects of sweepback and thickness ratio on the wing loads of a wing in the presence of a body has been made in the Langley 8-foot transonic pressure tunnel. The tests covered wings with a thickness ratio of 6 percent for sweepback angles of 0, 25, and 45 degrees and a thickness ratio of 4 percent for an unswept wing.
