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Investigation Of The Effects Of Leading Edge Chord Extensions And Fences In Combination With Leading Edge Flaps On The Aerodynamic Characteristics At Mach Numbers Of 040 To 093 Of A 45c Sweptback Wing Of Aspect Ratio 4
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Book Synopsis 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 by : Kenneth P. Spreemann
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.
Book Synopsis 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 by : Kenneth P. Spreemann
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 1953 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Effects of Leading-edge Chord-extensions on the Aerodynamic and Control Characteristics of Two Sweptback Wings at Mach Numbers of 1.41, 1.62, and 1.96 by : Ellery B. Jr May
Download or read book Investigation of the Effects of Leading-edge Chord-extensions on the Aerodynamic and Control Characteristics of Two Sweptback Wings at Mach Numbers of 1.41, 1.62, and 1.96 written by Ellery B. Jr May and published by . This book was released on 1951 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation at High Subsonic Speeds of the Effects of Leading-edge Radius on the Aerodynamic Characteristics of a Sweptback-wing-fuselage Combination with Leading-edge Flaps and Chord-extensions by : Kenneth P. Spreemann
Download or read book Experimental Investigation at High Subsonic Speeds of the Effects of Leading-edge Radius on the Aerodynamic Characteristics of a Sweptback-wing-fuselage Combination with Leading-edge Flaps and Chord-extensions written by Kenneth P. Spreemann and published by . This book was released on 1955 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited investigation was made at high subsonic speeds to determine the effects of a wing leading-edge radius on the aerodynamic characteristics of a sweptback-wing-fuselage combination with leading-edge flaps and chord-extensions. The basic wing had 45 degree sweepback, aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil section. The leading-edge shapes considered consisted of a sharp leading edge, a normal airfoil leading edge, and a leading edge formed by using three times the normal radius and fairing the new nose contour smoothly into the normal airfoil. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.80 to 0.92 and an angle-of-attack range of -2 to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations with leading-edge flap deflections of 0 to 6 degrees.
Book Synopsis Investigation of the Effects of Leading-edge Flaps on the Aerodynamic Characteristics in Pitch at Mach Numbers from 0.40 to 0.93 of a Wing-fuselage Configuration with a 45 Degree Sweptback Wing of Aspect Ratio 4 by : Kenneth P. Spreemann
Download or read book Investigation of the Effects of Leading-edge Flaps on the Aerodynamic Characteristics in Pitch at Mach Numbers from 0.40 to 0.93 of a Wing-fuselage Configuration with a 45 Degree Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1953 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Leading-edge Chord-extensions on the Aerodynamic Characteristics of a 45 Degrees Sweptback Wing-fuselage Combination at Mach Numbers of 0.40 to 1.03 by : F.E. Jr West
Download or read book Effect of Leading-edge Chord-extensions on the Aerodynamic Characteristics of a 45 Degrees Sweptback Wing-fuselage Combination at Mach Numbers of 0.40 to 1.03 written by F.E. Jr West and published by . This book was released on 1953 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Leading-edge Chord-extensions on Subsonic and Transonic Aerodynamic Characteristics of Three Models Having 45 Degrees Sweptback Wings of Aspect Ratio 4 by : Kenneth W. Goodson
Download or read book Effect of Leading-edge Chord-extensions on Subsonic and Transonic Aerodynamic Characteristics of Three Models Having 45 Degrees Sweptback Wings of Aspect Ratio 4 written by Kenneth W. Goodson and published by . This book was released on 1953 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Leading-edge Chord-extensions on the Aerodynamic Characteristics of a 45 Sweptback Wing-fuselage Combination at Mach Numbers of 0.40 to 1.03 by :
Download or read book Effect of Leading-edge Chord-extensions on the Aerodynamic Characteristics of a 45 Sweptback Wing-fuselage Combination at Mach Numbers of 0.40 to 1.03 written by and published by . This book was released on 1953 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Leading-edge Chord-extensions on Subsonic and Transonic Aerodynamic Characteristics of Three Models Having 45 Degree Sweptback Wings of Aspect Ratio 4 by : Kenneth W. Goodson
Download or read book Effect of Leading-edge Chord-extensions on Subsonic and Transonic Aerodynamic Characteristics of Three Models Having 45 Degree Sweptback Wings of Aspect Ratio 4 written by Kenneth W. Goodson and published by . This book was released on 1953 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Systematic Study of the Effects of Leading-edge Chord-extensions on the Low-speed Longitudinal Stability Characteristics of Three 45 Degree Sweptback Wings by : H. Neale Kelly
Download or read book A Systematic Study of the Effects of Leading-edge Chord-extensions on the Low-speed Longitudinal Stability Characteristics of Three 45 Degree Sweptback Wings written by H. Neale Kelly and published by . This book was released on 1955 with total page 113 pages. Available in PDF, EPUB and Kindle. Book excerpt: A low-speed leading-edge chord-extension has been conducted in the Langley 19-foot pressure tunnel. In the course of the investigation, chord-extensions of various designs were tested on three 45 degree sweptback wings of aspect ratio 5 and taper ratio 0.28 incorporating different airfoil sections. The tests were made at a Reynolds number of 4,600,000 and a corresponding Mach number of 0.11.
Book Synopsis The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 [degrees] of Sweptback at Mach Numbers to 0.92 by : Fred A. Demele
Download or read book The Effects of an Inverse-taper Leading-edge Flap on the Aerodynamic Characteristics in Pitch of a Wing-body Combination Having an Aspect Ratio of 3 and 45 [degrees] of Sweptback at Mach Numbers to 0.92 written by Fred A. Demele and published by . This book was released on 1958 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Fences, Leading-edge Chord-extensions, Boundary-layer Ramps, and Trailing-edge Flaps on the Longitudinal Stability of a Twisted and Cambered 60 Degree Sweptback-wing - Indented-body Configuration at Transonic Speeds by : Thomas L. Fischetti
Download or read book Effects of Fences, Leading-edge Chord-extensions, Boundary-layer Ramps, and Trailing-edge Flaps on the Longitudinal Stability of a Twisted and Cambered 60 Degree Sweptback-wing - Indented-body Configuration at Transonic Speeds written by Thomas L. Fischetti and published by . This book was released on 1954 with total page 17 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Small-scale Transonic Investigation of the Effects of Full-span and Partial-span Leading-edge Flaps on the Aerodynamic Characteristics of a 50 Degree 38' Sweptback Wing of Aspect Ratio 2.98 by : Kenneth P. Spreemann
Download or read book Small-scale Transonic Investigation of the Effects of Full-span and Partial-span Leading-edge Flaps on the Aerodynamic Characteristics of a 50 Degree 38' Sweptback Wing of Aspect Ratio 2.98 written by Kenneth P. Spreemann and published by . This book was released on 1952 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Leading-edge Droop on the Aerodynamic and Loading Characteristics of a 4-percent-thick Unswept-wing-fuselage Combination at Transonic Speeds by : James W. Schmeer
Download or read book Effect of Leading-edge Droop on the Aerodynamic and Loading Characteristics of a 4-percent-thick Unswept-wing-fuselage Combination at Transonic Speeds written by James W. Schmeer and published by . This book was released on 1956 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 16-foot transonic tunnel to determine the effects of leading-edge droop on the aerodynamic and loading characteristics of an unswept wing with a taper ratio of 0.5, an aspect ratio of 4, an NACA 65A004 airfoil sections parallel to the plane of symmetry. The leading edge of the wing was drooped both 6 and 10 degrees about the 17-percent-chord line, full span. Force, moment, and pressure measurements were obtained at Mach numbers from 0.60 to 1.05 and angles of attack, depending on Mach number, from approximately 0 to 16 degrees. The Reynolds number, based on the mean aerodynamic chord, varied from 4,600,000 to 6,300,000.
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