Download or read book Wind tunnel Investigation at Low Speed of Lateral Control Characteristics of an Untapered 45 Degrees Sweptback Semispan Wing of Aspect Ratio 1 59 Equipped with Various 25 percent chord Plain Ailerons written by Harold S. Johnson and published by . This book was released on 1951 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Low Speed of Lateral Control Characteristics of an Untapered 45 degress Sweptback Semispan Wing of Aspect Ratio 1 59 Equipped with Various 25 percent chord Plain Ailerons written by Harold S. Johnson and published by . This book was released on 1950 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1952 with total page 810 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Low Speed of a 45 Sweptback Untapered Semispan Wing of Aspect Ratio 1 59 Equipped with Various 25 percent chord Plain Flaps written by Harold S. Johnson and published by . This book was released on 1950 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at High Subsonic Speeds of the Lateral control Characteristics of an Aileron and a Stepped Spoiler on a Wing with Leading Edge Swept Back 51 3 Degrees written by Leslie E. Schneiter and published by . This book was released on 1949 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation has been made through a speed range from a Mach number of approximately 0.90 to determine the lateral-control characteristics of a 2-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoiler on a semispan-wing model with aspect ratio of 3.06 having 51.3 degree sweepback of the wing leading edge. In addition, the aerodynamic characteristics of the plain wing were determined through the speed range.
Download or read book Low speed Wind tunnel Investigation of Jet Control on a 35 Swept Wing written by John G. Lowry and published by . This book was released on 1953 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Low Speed of the Effect of Varying the Ratio of Body Diameter to Wing Span from 0 1 to 0 8 on the Aerodynamic Characteristics in Pitch of the 45 Sweptback wing body Combination written by Harold S. Johnson and published by . This book was released on 1953 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low speed Wind Tunnel as Affected by the Tunnel Walls written by Robert E. Dannenberg and published by . This book was released on 1950 with total page 678 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.
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.
Download or read book Wind tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack Up to 13 and at High Subsonic Mach Numbers 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 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
Download or read book A Wind tunnel Investigation at Low Speed of Various Lateral Controls on a 45 Degree Swept back Wing written by Edward J. Hopkins and published by . This book was released on 1948 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Some Low speed Wind tunnel Experiments Pertaining to the Longitudinal Stability Characteristics of a 35 Swept wing Model and an Unswept wing Model written by Byron M. Jaquet and published by . This book was released on 1953 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Low Speed Wind Tunnel Investigation of the Stability and Control Characteristics of a Series of Flying Wings with Sweep Angles of 60 Deg written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11-18 with total page 160 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel investigation was conducted in the Langley 12-Foot Low-Speed Wind Tunnel to study the low-speed stability and control characteristics of a series of four flying wings over an extended range of angle of attack (-8 deg to 48 deg). Because of the current emphasis on reducing the radar cross section of new military aircraft, the planform of each wing was composed of lines swept at a relatively high angle of 60 deg, and all the trailing-edge lines were aligned with one of the two leading edges. Three arrow planforms with different aspect ratios and one diamond planform were tested. The models incorporated leading-edge flaps for improved pitching-moment characteristics and lateral stability and had three sets of trailing-edge flaps that were deflected differentially for roll control, symmetrically for pitch control, and in a split fashion for yaw control. Top bodies of three widths and twin vertical tails of various sizes and locations were also tested on each model. A large aerodynamic database was compiled that could be used to evaluate some of the trade-offs involved in the design of a configuration with a reduced radar cross section and good flight dynamic characteristics. Moul, Thomas M. and Fears, Scott P. and Ross, Holly M. and Foster, John V. Langley Research Center AIRCRAFT DESIGN; DIRECTIONAL STABILITY; FLIGHT CHARACTERISTICS; LATERAL STABILITY; LEADING EDGE FLAPS; LOW SPEED STABILITY; RADAR CROSS SECTIONS; SWEPTBACK WINGS; TAIL ASSEMBLIES; TAILLESS AIRCRAFT; TRAILING EDGE FLAPS; WIND TUNNEL TESTS; ANGLE OF ATTACK; ASPECT RATIO; LEADING EDGES; PITCHING MOMENTS; ROLLING MOMENTS; TRADEOFFS; TRAILING EDGES; YAW...
Download or read book Wind Tunnel Investigation at Low Speed of the Effect of Varying the Ratio of Body Diameter to Wing Span from 0 1 to 0 8 on the Aerodynamic Characteristics in Pitch of a 45 Degree Sweptback wing body Combination written by Harold S. Johnson and published by . This book was released on 1953 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation at Low Speed of a Twisted and Cambered Wing Swept Back 63 Degrees with Vortex Generators and Fences written by James A. Weilberg and published by . This book was released on 1952 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Wind tunnel Investigation of the Low speed Longitudinal and Lateral Control Characteristics of a Triangular wing Model of Aspect Ratio 2 31 Having Constant chord Control Surfaces written by Walter D. Wolhart and published by . This book was released on 1950 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt:
