Download or read book Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degrees Sweptback Wing of Aspect of Aspect Ratio 3 Having a Full span Flap tyre Control written by Vernard E. Lockward and published by . This book was released on 1951 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3 Having a Full span Flap type Control written by Vernard E. Lockwood and published by . This book was released on 1951 with total page 35 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics in pitch and the control characteristics of a wing-flap combination have been determined for a wing having a quarter-chord line sweep of 45.58 degrees, an aspect ratio of 3, a taper ratio of 0.5, and an NACA 64A010 airfoil section measured in a plane at an angle of 45 degrees to the plane of symmetry. The wing employed a 25.4-percent-chord full-span plain flap-type control with a removable seal so that the effects of a relatively small gap could be determined. The investigation covered a Mach number range from 0.6 to 1.17 at angles of attack of 0, 4, and 8 degrees through a control-surface deflection range from -27 degrees to approximately 5 degrees. These data were obtained from the Langley high-speed 7- by 10-foot-tunnel transonic bump.

Download or read book Aerodynamic Characteristics at Transonic Speeds of a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 Having a Full span Flap Type of Control with Overhang Balance written by Vernard E. Lockwood and published by . This book was released on 1952 with total page 24 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 Aerodynamic Characteristics of a Spoiler slot deflector Control on a 45 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 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.61 and 2.01 to determine the aerodynamic characteristics of a spoiler-slot-deflector control on a 45 degree sweptback wing having an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. The model was equipped with a 15-percent-chord spoiler-slot-deflector extending from 13 o 78 percent of the wing semispan. The spoiler and deflector were hinged along the 60- and 75-percent-chord lines, respectively. Tests were made at a Reynolds number of 3,000,000 (based on the mean aerodynamic chord of the wing) and covered ranges of angles of attack from -3 to 15 degrees, spoiler projections from 0 to 8.0 percent chord, and deflector projections from 0 to 7.6 percent chord.

Download or read book Aerodynamic Characteristics at Transonic Speeds of a Wing Having a 45 Degree Sweep Aspect Ratio 8 Taper Ratio 0 45 and Airfoil Sections Varying from the NACA 63A010 Section at the Root to the NACA 63A006 Section at the Tip written by William D. Morrison and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley High-Speed 7- by 10-foot tunnel to determine the transonic aerodynamic characteristics of a wing having a spanwise variation in thickness ratio. The wing investigated had 45 degrees of sweepback, aspect ratio 8, taper ratio of 0.45, and airfoil sections tapered from an NACA 63A010 section at the root chord to an NACA 63A006 section at the tip chord. The test Mach number range was from 0.60 to 1.05 at Reynolds numbers of the order of 500,000.

Download or read book Control Characteristics at Transonic Speeds of a Linked Flap and Spoiler on a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 written by Vernard E. Lockwood and published by . This book was released on 1952 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Aerodynamic Characteristics at Transonic Speeds of an All movable Tapered 45 Degree Sweptback Aspect ratio 4 Tail Deflected about a Skewed Hinge Axis and Equipped with an Inset Unbalancing Tab written by James M. Watson 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 Hinge moment and Other Aerodynamic Characteristics at Transonic Speeds of a Quarter span Spoiler on a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3 written by Joseph E. Fikes and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Transonic Aerodynamic Characteristics of a Wing body Combination Having a 52 20 Sweptback Wing of Aspect Ratio 3 with Conical Camber and Designed for a Mach Number of 2 written by William B. Igoe and published by . This book was released on 1961 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics at Transonic Speeds of a Wing Having 45 Degrees Sweep Aspect Ratio 8 Taper Ratio 0 45 and Airfoil Sections Varying from the NACA 63A010 Section at the Root to the NACA 63A006 Section at the Tip written by William D. Jr Morrison and published by . This book was released on 1952 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book An Investigation at Transonic Speeds of the Effects of Thickness Ratio and of Thickened Root Sections on the Aerodynamic Characteristics of Wings with 47 Sweepback Aspect Ratio 3 5 and Taper Ratio 0 2 in the Slotted Test Section of the Langley 8 foot High speed Tunnel written by Ralph P. Bielat and published by . This book was released on 1951 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Four wing-body combinations of the same plan form (47 degree sweep, 3.5 aspect ratio, and 0.2 taper ratio) were compared at transonic speeds in the Langley 8-foot high-speed tunnel. Three wings were 4, 6, and 9 percent thick; the fourth was 6 percent thick but, on the inner 0.4 span, tapered to 12-percent thickness at the roots.

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Ross B. Robinson and published by . This book was released on 1952 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

Download or read book Effects of Spanwise Thickness Variation on the Aerodynamic Characteristics of 35 Degree and 45 Degree Sweptback Wings of Aspect Ratio 6 written by William D. Morrison and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: An aerodynamic investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamics characteristics of wings having 35 and 45 degrees of sweep-back, aspect ratio 6, and taper ratio 0.60. The wings were tapered from NACA 65A009 airfoil sections at the root chord to NACA 65A003 airfoil sections at the tip chord. The test Mach number range was from 0.60 to 1.14 at a Reynolds number of the order of 500,000.

Download or read book Aerodynamic Characteristics at Supersonic Speeds of a Series of Wing body Combinations Having Cambered Wings with an Aspect Ratio of 3 5 and a Taper Ratio of 0 2 written by Lowell E. Hasel and published by . This book was released on 1952 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Comparison of the Aerodynamic Characteristics at Transonic Speeds of a Plane Wing and a Cambered and Twisted Wing Both Having 45 Degrees of Sweepback and an Aspect Ratio of 6 written by George H. Holdaway and published by . This book was released on 1953 with total page 49 pages. Available in PDF, EPUB and Kindle. Book excerpt: