Flutter Investigation At Low Speed Of A 40 Degree Sweptback Wing With Pylon Mounted Stores Tested As A Semispan Cantilever Wing And As A Full Span Wing On A Towed Airplane Model

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Flutter Investigation at Low Speed of a 40 Degree Sweptback Wing with Pylon-mounted Stores, Tested as a Semispan-cantilever Wing and as a Full-span Wing on a Towed Airplane Model

Albert P. Martina
Flutter Investigation at Low Speed of a 40 Degree Sweptback Wing with Pylon mounted Stores Tested as a Semispan cantilever Wing and as a Full span Wing on a Towed Airplane Model Book PDF

Author : Albert P. Martina
Publisher : Unknown
Page : 38 pages
File Size : 53,9 Mb
Release : 1956
Category : Airplanes
ISBN : UOM:39015086466045

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Flutter Investigation at Low Speed of a 40 Degree Sweptback Wing with Pylon-mounted Stores, Tested as a Semispan-cantilever Wing and as a Full-span Wing on a Towed Airplane Model by Albert P. Martina Pdf

Wind-tunnel flutter investigations at Mach numbers up to 0.30 have been conducted on a 40 degree sweptback wing having pylon-mounted stores located at 73.5 percent of the semispan. The investigations were conducted on a semispan-cantilever wing with root fixed and with the full-span wing mounted on an autopilot-controlled model of a fighter-type airplane flown on the end of a towline. The store loadings were varied from 55 to 88 percent of the wing-panel weight, and the store pitch inertias were varied from 66 to 181 percent of the wing-panel pitch inertia. Most of the data were obtained with the store centers of gravity located at 15 percent of the local wing chord.

Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0.6

George W. Jones
Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0 6 Book PDF

Author : George W. Jones
Publisher : Unknown
Page : 22 pages
File Size : 45,7 Mb
Release : 1957
Category : Aerodynamics, Transonic
ISBN : UOM:39015086466078

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Investigation of Transonic Flutter Characteristics of a Thin 10 Degree Sweptback Wing Having an Aspect Ratio of 4 and a Taper Ratio of 0.6 by George W. Jones Pdf

A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers between 0.79 and 1.34 on a thin 10 degree sweptback wing having an aspect ratio of 4 and a taper ratio of 0.6. The data obtained have been compared with data from NACA Research Memorandum L55I13A for zero and 30 degree sweptback wings of the type investigated, the flutter boundary for the 10 degree sweptback wing falls between those for the zero degree and 30 degree sweptback wings in the low supersonic Mach number range. However, the subsonic level (around a Mach number of 0.8) of the flutter boundary for the 10 degree sweptback wing lies above those for the zero and 30 degree sweptback wings. In addition, the amount of rise in the flutter boundary from the subsonic level to the supersonic values is about the same for the wings with angles of sweepback of 10 degrees and zero degrees, but is much greater for the wing with an angle of sweepback of 30 degrees.

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

Jack F. Runckel
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 Book PDF

Author : Jack F. Runckel
Publisher : Unknown
Page : 104 pages
File Size : 45,7 Mb
Release : 1956
Category : Aerodynamic load
ISBN : UOM:39015095100999

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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 Pdf

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.

Wind-tunnel Investigation at Low Speed of Lateral Control Characteristics of an Untapered 45° Sweptback Semispan Wing of Aspect Ratio 1.59 Equipped with Various 25-percent-chord Plain Ailerons

Harold S. Johnson
Wind tunnel Investigation at Low Speed of Lateral Control Characteristics of an Untapered 45 Sweptback Semispan Wing of Aspect Ratio 1 59 Equipped with Various 25 percent chord Plain Ailerons Book PDF

Author : Harold S. Johnson
Publisher : Unknown
Page : 38 pages
File Size : 40,6 Mb
Release : 1951
Category : Aerofoils
ISBN : UOM:39015086495267

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Wind-tunnel Investigation at Low Speed of Lateral Control Characteristics of an Untapered 45° Sweptback Semispan Wing of Aspect Ratio 1.59 Equipped with Various 25-percent-chord Plain Ailerons by Harold S. Johnson Pdf

A wind-tunnel investigation at low speed was made to determine the lateral control characteristics of a 45 degree sweptback untapered semispan wing of aspect ratio 1.59 equipped with various 25-percent-chord plain unsealed ailerons. Variations of the lateral-control data with aileron span and spanwise location were determined through a large aileron-deflection range for various angles of attack up to about the angle of maximum lift.

Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing

Arvid L. Keith
Low speed Wind tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing Book PDF

Author : Arvid L. Keith
Publisher : Unknown
Page : 76 pages
File Size : 43,7 Mb
Release : 1950
Category : Air ducts
ISBN : UOM:39015086464701

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Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing by Arvid L. Keith Pdf

A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.

Flutter Investigation of Two Thin, Low-aspect-ratio, Swept, Solid, Metal Wings in the Transonic Range by Use of Free-falling Body

W. T. Lauten,Maurice A. Sylvester
Flutter Investigation of Two Thin Low aspect ratio Swept Solid Metal Wings in the Transonic Range by Use of Free falling Body Book PDF

Author : W. T. Lauten,Maurice A. Sylvester
Publisher : Unknown
Page : 18 pages
File Size : 50,7 Mb
Release : 1952
Category : Airplanes
ISBN : UOM:39015086464826

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Flutter Investigation of Two Thin, Low-aspect-ratio, Swept, Solid, Metal Wings in the Transonic Range by Use of Free-falling Body by W. T. Lauten,Maurice A. Sylvester Pdf

Flight Tests of a Leading-edge Area Suction on a Fighter-type Airplane with a 35 Degree Sweptback Wing

Richard S. Bray,Robert C. Innis
Flight Tests of a Leading edge Area Suction on a Fighter type Airplane with a 35 Degree Sweptback Wing Book PDF

Author : Richard S. Bray,Robert C. Innis
Publisher : Unknown
Page : 34 pages
File Size : 45,6 Mb
Release : 1955
Category : Aeronautics
ISBN : UOM:39015086432781

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Flight Tests of a Leading-edge Area Suction on a Fighter-type Airplane with a 35 Degree Sweptback Wing by Richard S. Bray,Robert C. Innis Pdf

Tests have been made to determine the flight characteristics of an F-86F airplane equipped with a leading-edge area-suction boundary-layer-control system, and to investigate the possible operational limitations imposed on a fighter-type airplane by such an installation. The results of the flight tests are compared with those of full-scale wind-tunnel tests of a similar installation on a model incorporating F-86 wing panels. The basic porous-area distribution tested extended the full length of the wing leading edge. Suction power was provided by a modified turbosupercharger which was driven by air bled from the compressor of the airplane's jet engine.

Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35©, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section

Robert F. Thompson
Lateral control Investigation of Flap type Controls on a Wing with Quarter chord Line Sweptback 35 Aspect Ratio 4 Taper Ratio 0 6 and NACA 65A006 Airfoil Section Book PDF

Author : Robert F. Thompson
Publisher : Unknown
Page : 28 pages
File Size : 40,8 Mb
Release : 1950
Category : Aerofoils
ISBN : UOM:39015086490557

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Lateral-control Investigation of Flap-type Controls on a Wing with Quarter-chord Line Sweptback 35©, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section by Robert F. Thompson Pdf

This paper presents the results of an investigation to determine the control-effectiveness characteristics of 30-percent-chord flap-type control surfaces of various spans on a semispan wing-fuselage model. The wing of the mode had 35 degrees of sweepback of the quarter chord, an aspect ratio of 4.0, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. Lift, rolling moments, and pitching moments were obtained for several angle of attack throughout a small range of control-surface deflections. Most of the data are presented as control-effectiveness parameters which show their variation with Mach number.

Transonic Flight Tests to Compare the Zero-lift Drag on Underslung and Symmetrical Nacelles Varied Chordwise at 40 Percent Semispan of a 45© Sweptback, Tapered Wing

William B. Pepper,Sherwood Hoffman
Transonic Flight Tests to Compare the Zero lift Drag on Underslung and Symmetrical Nacelles Varied Chordwise at 40 Percent Semispan of a 45 Sweptback Tapered Wing Book PDF

Author : William B. Pepper,Sherwood Hoffman
Publisher : Unknown
Page : 40 pages
File Size : 45,7 Mb
Release : 1950
Category : Airplanes
ISBN : UOM:39015086464685

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Transonic Flight Tests to Compare the Zero-lift Drag on Underslung and Symmetrical Nacelles Varied Chordwise at 40 Percent Semispan of a 45© Sweptback, Tapered Wing by William B. Pepper,Sherwood Hoffman Pdf

Subsonic Flutter Characteristics of a Variable Sweep Wing and Horizontal Tail Combination

Walter J. Mykytow,Thomas Edwin Noll,Lawrence J. Huttsell,Michael H. Shirk
Subsonic Flutter Characteristics of a Variable Sweep Wing and Horizontal Tail Combination Book PDF

Author : Walter J. Mykytow,Thomas Edwin Noll,Lawrence J. Huttsell,Michael H. Shirk
Publisher : Unknown
Page : 112 pages
File Size : 54,9 Mb
Release : 1970
Category : Aerodynamics
ISBN : UOM:39015095307016

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Subsonic Flutter Characteristics of a Variable Sweep Wing and Horizontal Tail Combination by Walter J. Mykytow,Thomas Edwin Noll,Lawrence J. Huttsell,Michael H. Shirk Pdf

The project concerns a subsonic investigation of a new type of flutter phenomenon, not previously critical from a design standpoint, involving elastic modes of the wing, fuselage, and stabilizer combination and also involving aerodynamic interference between the wing and horizontal tail. The effort, consisting of design of a flutter model, vibration and subsonic wind tunnel tests, and flutter analyses, was conducted to determine important controlling flutter parameters, to evaluate the accuracy of analyses for predicting the phenomenon, to establish flutter trends and to define flutter prevention design criteria which could be used in the early design stage to avoid the problem. Some of the important features that were determined are increasing wing sweep can lead to lower flutter speeds; wing bending to fuselage torsion frequency ratios were defined which provide the mechanical coupling essential to produce the phenomenon and minimum flutter speeds as a function of wing sweep angle; vertical separation or dihedral angle can be very influential and beneficial and is more important than longitudinal separation, the effects of which were found to be small to moderate; the effects of compressibility have been shown to be detrimental and decrease the flutter speed, and conclusive proof that the interference aerodynamics between the wind and tail, and particularly, the downwash shed from the wing, is an important and detrimental feature to the phenomenon. (Author).