Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Wind Tunnel Investigation At High Subsonic Speeds Of The Effect Of Spoiler Profile On The Lateral Control Characteristics Of A Wing Fuselage Combination Winter Quarter Chord Line Swept Back 326c And Naca 65a006 Airfoil Section
Download Wind Tunnel Investigation At High Subsonic Speeds Of The Effect Of Spoiler Profile On The Lateral Control Characteristics Of A Wing Fuselage Combination Winter Quarter Chord Line Swept Back 326c And Naca 65a006 Airfoil Section full books in PDF, epub, and Kindle. Read online Wind Tunnel Investigation At High Subsonic Speeds Of The Effect Of Spoiler Profile On The Lateral Control Characteristics Of A Wing Fuselage Combination Winter Quarter Chord Line Swept Back 326c And Naca 65a006 Airfoil Section ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4 by : Paul G. Fournier
Download or read book Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a Wing-fuselage Combination Having a Triangular Wing of Aspect Ratio 4 written by Paul G. Fournier and published by . This book was released on 1953 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results presented in the present paper are part of a program conducted to investigate the effect of wing plan form on the aerodynamic characteristics in pitch, in sideslip, and during steady roll. This paper presents the aerodynamic characteristics in pitch and sideslip at high subsonic speeds of a wing-fuselage combination having a triangular wing of aspect ratio 4, a leading-edge sweep of angle of 45 degrees, and with an NACA 65A006 airfoil section parallel to the plane of symmetry.
Book Synopsis Wind-tunnel Investigation of the Static Lateral Stability Characteristics of Wing-fuselage Combinations at High Supersonic Speeds by : Paul G. Fournier
Download or read book Wind-tunnel Investigation of the Static Lateral Stability Characteristics of Wing-fuselage Combinations at High Supersonic Speeds written by Paul G. Fournier and published by . This book was released on 1953 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wind-tunnel Investigation at High Subsonic Speeds to Determine the Rolling Derivatives of Two Wing-fuselage Combinations Having Triangular Winds, Including a Semiempirical Method of Estimating the Rolling Derivatives by : James W. Wiggins
Download or read book Wind-tunnel Investigation at High Subsonic Speeds to Determine the Rolling Derivatives of Two Wing-fuselage Combinations Having Triangular Winds, Including a Semiempirical Method of Estimating the Rolling Derivatives written by James W. Wiggins and published by . This book was released on 1954 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics of a Spoiler-slot-deflector Control on a 45° Sweptback-wing-fuselage Model at High Subsonic Speeds by : Alexander D. Hammond
Download or read book Aerodynamic Characteristics of a Spoiler-slot-deflector Control on a 45° Sweptback-wing-fuselage Model at High Subsonic Speeds written by Alexander D. Hammond and published by . This book was released on 1960 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Book Synopsis Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing by : Edward C. Polhamus
Download or read book Effect at High Subsonic Speeds of Fuselage Forebody Strakes on the Static Stability and Vertical-tail-load Characteristics of a Complete Model Having a Delta Wing written by Edward C. Polhamus and published by . This book was released on 1958 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation at high subsonic speeds has been conducted to determine the effect of fuselage forebody strakes on the static stability and the vertical-tail-load characteristics of an airplane-type configuration having a delta wing. The tests were made at Mach numbers from 0.60 to 0.92 corresponding to Reynolds numbers from 3,000,000 to 4,200,000, based on the wing mean aerodynamic chord, and at angles of attack from approximately -2 to 24 degrees.
Book Synopsis A Buffet Investigation at High Subsonic Speeds of Wing-fuselage-tail Combinations Having Sweptback Wings with NACA 64A Thickness Distributions, Fences, a Leading-edge Extension, and Body Contouring by : Fred B. Sutton
Download or read book A Buffet Investigation at High Subsonic Speeds of Wing-fuselage-tail Combinations Having Sweptback Wings with NACA 64A Thickness Distributions, Fences, a Leading-edge Extension, and Body Contouring written by Fred B. Sutton and published by . This book was released on 1957 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made to determine the effect of wing fences, a wing leading-edge extension, changing wing sweepback angle from 40 to 45 and 50 degrees, fuselage contouring, and varying horizontal tail height upon the buffeting response of some typical airplane configurations employing sweptback wings with high aspect ratios. The tests were conducted through an angle-of-attack range at Mach numbers varying from 0.60 to 0.92 at a Reynolds number of 2 million.
Book Synopsis Wind-tunnel Investigation of the Static Lateral Stability Characteristics of Wing-fuselage Combinations at High Subsonic Speeds by : James W. Wiggins
Download or read book Wind-tunnel Investigation of the Static Lateral Stability Characteristics of Wing-fuselage Combinations at High Subsonic Speeds written by James W. Wiggins and published by . This book was released on 1957 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section by : Boyd C. Myers
Download or read book Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.3, and NACA 65A006 Airfoil Section written by Boyd C. Myers and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.
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.
