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Pressure Distributions Over A Retracted Leading Edge Slat On A 40 Degree Sweptback Wing At Mach Numbers Up To 09
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Book Synopsis Pressure Distributions Over a Retracted Leading-edge Slat on a 40 Degree Sweptback Wing at Mach Numbers Up to 0.9 by : Jones F. Cahill
Download or read book Pressure Distributions Over a Retracted Leading-edge Slat on a 40 Degree Sweptback Wing at Mach Numbers Up to 0.9 written by Jones F. Cahill and published by . This book was released on 1951 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distributions over a retracted leading-edge slat on a 40 degree sweptback wing are presented for a series of angles of attack up to maximum lift at Mach numbers of 0.1, 0.4, 0.6, 0.7, 0.8, 0.85, and 0.9. These data were obtained in the Langley low-turbulence pressure tunnel at a constant Reynolds number of approximately 3,000,000. The Reynolds number was maintained approximately constant through the Mach number range by varying the stagnation pressure.
Book Synopsis Aerodynamic Characteristics of a Leading-edge Slat on a 35 Degree Swept-back Wing for Mach Numbers from 0.30 to 0.88 by : John A. Kelly
Download or read book Aerodynamic Characteristics of a Leading-edge Slat on a 35 Degree Swept-back Wing for Mach Numbers from 0.30 to 0.88 written by John A. Kelly and published by . This book was released on 1951 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The data presented in this report were obtained by North American Aviation, Inc., from an investigation conducted in the Southern California Cooperative Wind Tunnel. Tests were made over a range of Mach numbers from 0.300 to 0.883 to determine the aerodynamic characteristics of a semispan model of a 35 degree swept-back wing equipped with a leading-edge slat and to gain additional knowledge of the aerodynamic loads and automatic operation of the slat. Lift, drag, and pitching-moment characteristics of a model wing in the presence of a fuselage were measured as well as pressures acting on the slat in the retracted and the full-open positions. The pressure data were analyzed to ascertain the opening characteristics of the slat for two possible circular-arc slat tracks which could be used for automatic operation of the slat.
Book Synopsis Aerodynamic Load Measurements Over a Leading-edge Slat on a 40 Degree Sweptback Wing at Mach Numbers from 0.10 to 0.91 by : Jones F. Cahill
Download or read book Aerodynamic Load Measurements Over a Leading-edge Slat on a 40 Degree Sweptback Wing at Mach Numbers from 0.10 to 0.91 written by Jones F. Cahill and published by . This book was released on 1952 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Load Measurements and Opening Characteristics of Automatic Leading-edge Slats on a 45 Degree Sweptback Wing at Transonic Speeds by : Donald D. Arabian
Download or read book Aerodynamic Load Measurements and Opening Characteristics of Automatic Leading-edge Slats on a 45 Degree Sweptback Wing at Transonic Speeds written by Donald D. Arabian and published by . This book was released on 1961 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 by : Peter T. Bernot
Download or read book Pressure Distributions on Blunt-delta Wings at Angles of Attack Up to 90 Degrees and Mach Number of 6.85 written by Peter T. Bernot and published by . This book was released on 1963 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 by : Marvin Kussoy
Download or read book Local Pressure Distribution on a Blunt Delta Wing for Angles of Attack Up to 35 Degrees at Mach Numbers of 3.4 and 4.7 written by Marvin Kussoy and published by . This book was released on 1962 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions and Aerodynamic Characteristics of Several Spoiler Controls on a 40 Degree Sweptback Wing at a Mach Number of 1.61 by : Emma Jean Landrum
Download or read book Pressure Distributions and Aerodynamic Characteristics of Several Spoiler Controls on a 40 Degree Sweptback Wing at a Mach Number of 1.61 written by Emma Jean Landrum and published by . This book was released on 1960 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effect of Leading-edge Droop Upon the Pressure Distribution and Aerodynamic Loading Characteristics of a 45 Degree Sweptback Wing at Transonic Speeds by : James W. Schmeer
Download or read book The Effect of Leading-edge Droop Upon the Pressure Distribution and Aerodynamic Loading Characteristics of a 45 Degree Sweptback Wing at Transonic Speeds written by James W. Schmeer and published by . This book was released on 1955 with total page 42 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 pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The leading edge of the wing was drooped 6 degrees about the 19-percent chord line from 0.15 semispan to the wing tip. Data were obtained at Mach numbers of 0.80 to 1.03 with average Reynolds numbers of 5,700,000 to 6,300,000, respectively. The results of this investigation are compared with the pressure data obtained with the undrooped or basic wing of a previous investigation.
Book Synopsis Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 by : Barry Moskowitz
Download or read book Experimental Pressure Distributions Over Two Wing-body Combinations at Mach Number 1.9 written by Barry Moskowitz and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Pressure distributions on two wing-body combinations were obtained at Mach number of 1.9 to investigate wing-body interference. A rectangular wing, a triangular wing, and a cylindrical body having an ogive nose were investigated alone and in combination. Pressure distributions over the wing body combination compared favorable with theoretical calculations based primarily on a generalization of the method of Nielsen and Matteson, except at the root section of wings where boundary layer of body modified the flow.
Book Synopsis Analysis of Pressure Distributions for a Series of Controls on a 40 Deg Sweptback Wing at a Mach Number of 1.61 by :
Download or read book Analysis of Pressure Distributions for a Series of Controls on a 40 Deg Sweptback Wing at a Mach Number of 1.61 written by and published by . This book was released on 1959 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of Pressure Distribution Over an Extended Leading-Edge Flap on a 42 Degree Sweptback Wing by :
Download or read book Investigation of Pressure Distribution Over an Extended Leading-Edge Flap on a 42 Degree Sweptback Wing written by and published by . This book was released on 1947 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: Pressure distribution over an extended leading-edge flap on a 42 degree swept-back wing was investigated. Results indicate that the flap normal-force coefficient increased almost linearly with the angle of attack to a maximum value of 3.25. The maximum section normal-force coefficient was located about 30 percent of the flap span outboard of the inboard end and had a value of 3.75. Peak negative pressures built up at the flap leading edge as the angle of attack was increased and caused the chordwise location of the flap center of pressure to be move forward.
Book Synopsis Pressure Distribution at Mach Numbers Up to 0.90 on a Cambered and Twisted Wing Having 40 Degrees of Sweepback and an Aspect Ratio of 10, Including the Effects of Fences by : Frederick W. Boltz
Download or read book Pressure Distribution at Mach Numbers Up to 0.90 on a Cambered and Twisted Wing Having 40 Degrees of Sweepback and an Aspect Ratio of 10, Including the Effects of Fences written by Frederick W. Boltz and published by . This book was released on 1953 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure-distribution Measurements Over a 45 Degree Sweptback Wing at Transonic Speeds by the NACA Wing-flow Method by : Edward C. B. Danforth
Download or read book Pressure-distribution Measurements Over a 45 Degree Sweptback Wing at Transonic Speeds by the NACA Wing-flow Method written by Edward C. B. Danforth and published by . This book was released on 1951 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of pressure were made over the chord of a swept-wing model at four stations along (2, 6, 50, and 82 percent semispan) by the NACA wing-flow method. The model tested was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. The tests were conducted at Mach numbers from about 0.7 to 1.1 at angles of attack from -1 to 4 degrees. The Reynolds number of the tests was nominally 600,000 based on the wing chord in the stream direction. The results are presented to show the chordwise pressure distributions and the spanwise distributions of section lift, drag, and pitching moment.
Book Synopsis Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01 by : Douglas R. Lord
Download or read book Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01 written by Douglas R. Lord and published by . This book was released on 1957 with total page 335 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions at Mach Numbers from 1.6 to 2.8 of 74 Deg Swept Arrow Wings with and Without Camber and Twist by :
Download or read book Pressure Distributions at Mach Numbers from 1.6 to 2.8 of 74 Deg Swept Arrow Wings with and Without Camber and Twist written by and published by . This book was released on 1960 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Pressure Distributions at Mach Number 2.05 on a Series of Highly Swept Arrow Wings Employing Various Degrees of Twist and Camber by : Harry W. Carlson
Download or read book Pressure Distributions at Mach Number 2.05 on a Series of Highly Swept Arrow Wings Employing Various Degrees of Twist and Camber written by Harry W. Carlson and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
