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 of 0 40 to 0 93 of a 45 Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 56 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 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:

Download or read book Effects of Fences Leading edge Chord extensions Bound layer Ramps and Trailing edge Flaps on the Longitudinal Stability of a Twisted and Cambered 60 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 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

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:

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:

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:

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:

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:

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:

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:

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.

Download or read book Transonic Wind tunnel Investigation of the Effects of Aspect Ratio Spanwise Variations in Section Thickness Ratio and a Body Indentation on the Aerodynamic Characteristics of a 45 Sweptback Wing body Combination written by Melvin M. Carmel and published by . This book was released on 1953 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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 Sweepback 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: An investigation has been made to detemnine the effects of an inverse-taper leading-edge flap on the drag and on the static-longitudinal characteristics of a swept-wing-body conibination. The wing had 45 degrees of leading-edge sweepback, an aspect ratio of 3, a taper ratio of 0.4, and no camber or twist. However, with the flap deflected, the wing had a camber and twist distribution similar to that resulting from the incorporation of conical camber in the forward portion of a plane wing. The tests were conducted over a range of Mach numbers from 0.25 to 0.92 at a Reynolds number of 3.2 million, and over a Reynolds number range of 3.2 million to 15 million at a Mach number of 0.25 with flap deflections to 16 degrees.

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.

Download or read book Investigation of the Effects of an Airfoil Section Modification on the Aerodynamic Characteristics at Subsonic and Supersonic Speeds of a Thin Swept Wing of Aspect Ratio 3 in Combination with a Body written by David Graham and published by . This book was released on 1955 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation has been conducted to determine the effects of an airfoil section modification consisting of a greatly increased leading-edge radius and slight forward camber on the aerodynamic characteristics of a thin swept-wing-body combination at Mach numbers from 0.06 to 1.9. The basic wing had an aspect ratio of 3, taper ratio of 0.4, leading-edge sweep of 45 degrees, and an NACA 64A006 airfoil section perpendicular to the quarter-chord line. A large-scale model was tested at low speeds and at Reynolds numbers from 4,400,000 to 21,000,000 and a small-scale model was tested at high subsonic and supersonic speeds at Reynolds number from 2,900,000 to 5,700,000. Lift, drag, and pitching moment were measured.