Download or read book Transonic Aerodynamic Characteristics of Three W plan form Wings Having Aspect Ratio 8 Taper Ratio 0 45 and NACA 63A series Airfoil Sections written by William D. Jr Morrison and published by . This book was released on 1952 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by William C. Sleeman and published by . This book was released on 1949 with total page 36 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 Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 0 3 and NACA 65A006 Airfoil Section written by Boyd C. Myers and published by . This book was released on 1949 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper presents the results of the investigation of a wing-alone and wing-fuselage configuration employing a wing with the quarter-chord line swept back 45 degrees, with aspect ratio 4, taper ratio 0.3, and an NACA 65A006 airfoil section. Lift, drag, pitching moment, and root bending moment were obtained for these configurations. In addition, effective downwash angles and dynamic-pressure characteristics in the region of a probable tail location were also obtained for these configurations and are presented for a range of tail heights at one tail length. In order to expedite the publishing of these data, only a brief analysis is included.
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 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 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 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 Aerodynamic Characteristics of Tapered Wings Having Aspect Ratios of 4 6 and 8 Quarter chord Lines Swept Back 45 Degrees and NACA 63 sub 1 A012 Airfoil Sections written by Edward C. Polhamus and published by . This book was released on 1951 with total page 23 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of a transonic research program conducted by the National Advisory Committee for Aeronautics, a series of wings is being investigated in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.70 to 1.15 by use of the transonic-bump technique.
Download or read book WADC Technical Note written by United States. Wright Air Development Division and published by . This book was released on 1959 with total page 912 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Studies written by Zbiginew Krzywoblocki and published by . This book was released on 1957 with total page 266 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 Effect of Longitudinal Wings Position on the Pressure Characteristics at Transonic Speeds of a 45 Sweptback Wing fuselage Model written by William Solomon and published by . This book was released on 1953 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics of a Wing with Quarter chord Line Swept Back 45 Degrees Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section written by Joseph Weil and published by . This book was released on 1949 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: As part of an NACA research program, a series of wing-body combinations are being investigated in the Langley high-speed 7- by 10-foot tunnel up to a Mach number of 1.18 utilizing the transonic bump.
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 Two Leading edge Modifications on the Aerodynamic Characteristics of a Thin Low aspect ratio Delta Wing at Transonic Speeds written by John P. Mugler and published by . This book was released on 1956 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 8-foot transonic tunnel to determine the aerodynamic characteristics of a thin 60 degree delta wing with two leading-edge modifications (conical leading-edge camber and leading-edge droop) in combination with bodies with and without body indentation in accordance with the transonic-area-rule concept. The tests covered a Mach number range from 060 to 1.15 and an angle-of-attack range from -4 to 20 degrees at a Reynolds number of about 3,000,000 based on the wing mean aerodynamic chord. The wing had an aspect ratio of 2.31, a taper ratio of 0, and, without modifications, had NACA 65A003 airfoil sections parallel to the model plane of symmetry.
