Download or read book Small scale Transonic Investigation of a 45 Degrees Sweepback Wing of Aspect Ratio 4 with Combinations of Nose flap Deflections and Wing Twist written by William J. Jr Alford and published by . This book was released on 1953 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Effects of Leading edge Chord extensions and Fences in Combination with Leading edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0 40 to 0 93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt: This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
Download or read book Subject Index to Unclassified ASTIA Documents written by Defense Documentation Center (U.S.) and published by . This book was released on 1960 with total page 894 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Small scale Investigation at Transonic Speeds of the Effects of Thickening the Inboard Section of a 45 Degrees Sweptback Wing of Aspect Ratio 4 Taper Ratio 0 3 and NACA 65A006 Airfoil Section written by Kenneth P. Spreemann and published by . This book was released on 1951 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Transonic Investigation of a 45 Sweptback Wing body Combination with Several Types of Body Indentation with Theoretical Comparisons Included written by Melvin M. Carmel and published by . This book was released on 1954 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3 a Taper Ratio of 0 2 and NACA 65A004 Airfoil Sections written by Jack F. Runckel and published by . This book was released on 1956 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
Download or read book An Experimental Transonic Investigation of a 45 Degrees Sweptback Wing body Combination with Several Types of Body Indentation with Theoretical Comparisons Included written by Melvin M. Carmel and published by . This book was released on 1954 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0 6 written by George W. Jones and published by . This book was released on 1957 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.79 and 1.34 on a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6. The data obtained have been compared with data from NACA Research Memorandum L55I13A for zero and 30 degree sweptback wings of the type investigated, the flutter boundary for the 10 degree sweptback wing falls between those for the zero degree and 30 degree sweptback wings in the low supersonic Mach number range. However, the subsonic level (around a Mach number of 0.8) of the flutter boundary for the 10 degree sweptback wing lies above those for the zero and 30 degree sweptback wings. In addition, the amount of rise in the flutter boundary from the subsonic level to the supersonic values is about the same for the wings with angles of sweepback of 10 degrees and zero degrees, but is much greater for the wing with an angle of sweepback of 30 degrees.
Download or read book Investigation of Three Tapered 45 Degree Sweptback Cambered and Twisted Wings Covering a Simultaneous Variation in Aspect Ratio and Thickness Ratio and of One Related Symmetrical Wing at Transonic Speeds by the Wing flow Method written by Harold I. Johnson and published by . This book was released on 1953 with total page 55 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Small scale Transonic Investigation of the Effects of Twist and Camber on the Aerodynamic Characteristics of a 60 Degrees 42 Minutes Sweptback Wing of Aspect Ratio 1 94 written by Kenneth P. Spreeman and published by . This book was released on 1952 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Transonic Investigation of the Static Longitudinal stability Characteristics of a 45 Degree Sweptback Wing fuselage Combination with and Without Horizontal Tail written by Chris C. Critzos and published by . This book was released on 1956 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation of the static longitudinal-stability characteristics of a 45 degree sweptback wing-fuselage configuration has been conducted in the Langley 16-foot transonic tunnel. The wing had an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections parallel to the plane of symmetry. Data were obtained for the model with and with a sweptback horizontal tail for an angle-of-attack range from -4 to about 27 degrees and for Mach numbers ranging from 0.80 to 1.05. The Reynolds number varied from 6,000,000 to about 8,500,000.
Download or read book Aeronautical Engineering Review written by and published by . This book was released on 1957 with total page 844 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerospace Engineering written by and published by . This book was released on 1958-05 with total page 1236 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation at Transonic Speeds of the Loading Over a 45 Degree Sweptback Wing Having an Aspect Ratio of 3 a Taper Ratio of 0 2 and Naca 65a004 Airfoil Sections written by JACK F. RUNCKEL and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).
Download or read book Transonic Flutter Investigation of a Cantilevered Aspect ratio 4 45 Degree Sweptback Untapered Wing with Three Different Pylon mounted External Store Configurations written by Charles L. Ruhlin and published by . This book was released on 1957 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt: A brief, exploratory investigation has been made of the transonic flutter characteristics of a cantilevered, aspect-ratio-4, 45 degree sweptback, untapered wing with three different pylon-mounted external-store configuration. For stores located near the midsemispan and weighing about 0.7 of the semispan wing, the flutter speed was not changed when the store center of gravity was moved from 38 to 12 percent of the chord. The flutter speeds for these two stores were from 14 to 19 percent less than those obtained with the wings alone at subsonic speeds. The rate of rise of flutter speed with Mach number in the low supersonic range was about the same for the wing with stores as for the plain wing.
Download or read book Transonic Wind tunnel Investigation on the Effects of Taper Ratio and Body of a 45 Degrees Sweptback Wing in the Presence of a Body written by James B. Delano and published by . This book was released on 1955 with total page 53 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Flight Tests to Compare the Zero lift Drags of 45 Degrees Sweptback Wings of Aspect Ratio 3 55 and 6 0 with and Without Nacelles at the Wing Tips written by Sherwood Hoffman and published by . This book was released on 1952 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
