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Investigation At Transonic Speeds Of Loading Over A 30 Deg Sweptback Wing Of Aspect Ratio 3 Taper Ratio 02 And Naca 65a004 Airfoil Section Mounted On A Body
Download Investigation At Transonic Speeds Of Loading Over A 30 Deg Sweptback Wing Of Aspect Ratio 3 Taper Ratio 02 And Naca 65a004 Airfoil Section Mounted On A Body full books in PDF, epub, and Kindle. Read online Investigation At Transonic Speeds Of Loading Over A 30 Deg Sweptback Wing Of Aspect Ratio 3 Taper Ratio 02 And Naca 65a004 Airfoil Section Mounted On A Body ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis 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 by : Jack F. Runckel
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.
Book Synopsis Investigation at Transonic Speeds of Loading Over a 30° Sweptback Wing of Aspect Ratio 3, Taper 0.2, and NACA 65A004 Airfoil Section Mounted on a Body by : Donald D. Arabian
Download or read book Investigation at Transonic Speeds of Loading Over a 30° Sweptback Wing of Aspect Ratio 3, Taper 0.2, and NACA 65A004 Airfoil Section Mounted on a Body written by Donald D. Arabian and published by . This book was released on 1960 with total page 79 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation at Transonic Speeds of Loading Over a 30 Degree Sweptback Wing of Aspect Ratio 3, Taper Ratio 0.2, and NACA 65A004 Airfoil Section Mounted on a Body by : Donald D. Arabian
Download or read book Investigation at Transonic Speeds of Loading Over a 30 Degree Sweptback Wing of Aspect Ratio 3, Taper Ratio 0.2, and NACA 65A004 Airfoil Section Mounted on a Body written by Donald D. Arabian and published by . This book was released on 1957 with total page 79 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic load characteristics of a wing-body combination were determined experimentally from 0.80 to 1.03 Mach number for angles of attack up to 26 degrees. Two wings, both with 30 degree sweep of the quarter-chord line, taper ratio 0.2, aspect ratio 3, and thickness of 4 percent chord, but at different types of construction, were tested. One wing was of solid steel and the other was of plastic with an inner steel core.
Book Synopsis Investigation at Transonic Speeds of Loading Over a 30 Deg Sweptback Wing of Aspect Ratio 3, Taper Ratio 0.2, and NACA 65A004 Airfoil Section Mounted on a Body by : Donald D. Arabian
Download or read book Investigation at Transonic Speeds of Loading Over a 30 Deg Sweptback Wing of Aspect Ratio 3, Taper Ratio 0.2, and NACA 65A004 Airfoil Section Mounted on a Body written by Donald D. Arabian and published by . This book was released on 1960 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic load characteristics of a wing-body combination were determined experimentally at Mach numbers from 0.80 to 1.03 for angles of attack up to 26 degrees. Two wings, both with 30 degrees sweep of the quarter-chord line, taper ratio of 0.2, aspect ratio of 3, and thickness of 4 percent chord, but of different types of construction, were tested. One wing was of solid steel and the other was of plastic with an inner steel core ...
Book Synopsis 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 by : JACK F. RUNCKEL
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).
Book Synopsis Investigation at Transonic Speeds of the Loading Over a 40 Degree Sweptback Wing Having an Aspect Ratio of 3, a Taper Ratio of 0.2 and NACA 65A004 Airfoil Sections by : Jack F. Runckel
Download or read book Investigation at Transonic Speeds of the Loading Over a 40 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 93 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : Kenneth P. Spreemann
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:
Book Synopsis 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 by : Robert J. Platt
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.
Book Synopsis Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 by : Marlowe D. Cassetti
Download or read book Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 written by Marlowe D. Cassetti and published by . This book was released on 1961 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made of the effects of conical wing camber and body indentation according to the supersonic area rule on the aerodynamic wing loading characteristics of a wing-body-tail configuration at transonic speeds. The wing aspect ratio was 3, taper ratio was 0.1, and quarter-chord-line sweepback was 52.5° with 3-percent-thick airfoil sections. The tests were conducted in the Langley 16-foot transonic tunnel at Mach numbers from 0.80 to 1.05 and at angles of attack from 0° to 14°, with Reynolds numbers based on mean aerodynamic chord varying from 7 x 106 to 8 x 106. Conical camber delayed wing-tip stall and reduced the severity of the accompanying longitudinal instability but did not appreciably affect the spanwise load distribution at angles of attack below tip stall. Body indentation reduced to transonic chordwise center-of-pressure travel from about 8 percent to 5 percent of the mean aerodynamic chord.
Book Synopsis Loads on Thin Wings at Transonic Speeds by : Don D. Davis (Jr.)
Download or read book Loads on Thin Wings at Transonic Speeds written by Don D. Davis (Jr.) and published by . This book was released on 1955 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effect of a Change in Body Shape on the Loading of a 45 Degree Sweptback Wing-body Combination at Transonic Speeds by : Donald L. Loving
Download or read book The Effect of a Change in Body Shape on the Loading of a 45 Degree Sweptback Wing-body Combination at Transonic Speeds written by Donald L. Loving and published by . This book was released on 1954 with total page 67 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made in the Langley 8-foot transonic tunnel of the pressure distribution on a wing-body combination having a 45 degree swept-back wing with aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. The body had an afterbody which was cylindrical from the region of the leading edge of the wing-body juncture rearward to the base. Data were obtained at Mach number from 0.60 to 1.13. The test Reynolds numbers ranged from 1,740,000 to 2,030,000. In order to determine the effects on loads of a change in body shape, the results of this investigation are compared with similar data previously obtained for the same wing in combination with a body that was curved from the nose to the base.
Book Synopsis Lateral-control Investigation of Flat-type Controls on a Wing Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by : Robert F. Thomson
Download or read book Lateral-control Investigation of Flat-type Controls on a Wing Quarter-chord Line Swept Back 35 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section written by Robert F. Thomson and published by . This book was released on 1950 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Sweep on the Damping-in-roll Characteristics of Three Sweptback Wings Having an Aspect Ratio of 4 at Transonic Speeds by : Vernard E. Lockwood
Download or read book Effects of Sweep on the Damping-in-roll Characteristics of Three Sweptback Wings Having an Aspect Ratio of 4 at Transonic Speeds written by Vernard E. Lockwood and published by . This book was released on 1950 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: The damping-in-roll characteristics of three wings having an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil section, and sweep angles of 0, 35, and 45 degrees have been determined through a Mach number range from 0.6 to 1.15 and an angle-of-attack range from 0 to approximately 7 degrees. The data were obtained from the Langley 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique.
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 58 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.
Book Synopsis Transonic Wind-tunnel Investigation on the Effects of Taper Ratio and Body of a 45 Degrees Sweptback Wing in the Presence of a Body by : James B. Delano
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:
Book Synopsis Preliminary Investigation of Control Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Horn-balanced Full-span Control by : John G. Lowry
Download or read book Preliminary Investigation of Control Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Horn-balanced Full-span Control written by John G. Lowry and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Combined Effects of Wing Taper and Low Horizontal-tail Position on Longitudinal Stability of a 45 Degree Sweptback Wing-body Combination at Transonic Speeds by : Stanley H. Spooner
Download or read book Combined Effects of Wing Taper and Low Horizontal-tail Position on Longitudinal Stability of a 45 Degree Sweptback Wing-body Combination at Transonic Speeds written by Stanley H. Spooner and published by . This book was released on 1956 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The combined effects of wing taper ratio and low horizontal-tail position on the static longitudinal stability of a 45 degree sweptback wing-body combination with an aspect ratio of approximately 4 have been investigated for a range of Mach numbers from 0.8 to 1.2 in the Langley 8-foot transonic pressure tunnel.
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