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Wind Tunnel Investigation At Low Speed Of A Twisted And Cambered Wing Swept Back 63 Degrees With Vortex Generators And Fences Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of Wind Tunnel Investigation At Low Speed Of A Twisted And Cambered Wing Swept Back 63 Degrees With Vortex Generators And Fences book. This book definitely worth reading, it is an incredibly well-written.
Author : James A. Weilberg
Publisher : Unknown
Page : 64 pages
File Size : 43,6 Mb
Release : 1952
Category : Electronic
ISBN : NASA:31769000420458
Author : Arvid L. Keith
Publisher : Unknown
Page : 76 pages
File Size : 53,8 Mb
Release : 1950
Category : Air ducts
ISBN : UOM:39015086464701
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.
Author : John G. Lowry,Thomas R. Turner
Publisher : Unknown
Page : 18 pages
File Size : 45,6 Mb
Release : 1953
Category : Airplanes
ISBN : UOM:39015086465401
Author : John E. Lamar,L. Wayne McKinney
Publisher : Unknown
Page : 332 pages
File Size : 48,9 Mb
Release : 1971
Category : Airplanes
ISBN : UIUC:30112106882464
The experimental balance and pressure data obtained from tests of an untwisted variable-sweep wing with an outboard pivot exhibited nonlinearities in both total normalforce-coefficient and pitching-moment-coefficient curves for all sweep angles and fuselage conditions. These total effects have been traced back through the section data and pressure distributions to find the causes. The causes of these nonlinearities were found to be (1) separation of flow on the outer panel and (2) a leading-edge vortex flow on the inner panel. A fuselage added to the wing had little effect on the aerodynamic characteristics. Predictions of wing loadings and performance characteristics were made by using the modified Multhopp method and a comparison with experimental results indicated reasonable agreement. The changes in span loading as a result of leading-edge shed-vortex formation and flow separation at the higher angles of attack caused an increase in the induced-drag parameter.
Author : Anonim
Publisher : Unknown
Page : 52 pages
File Size : 40,6 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000458920
Author : Harold S. Johnson
Publisher : Unknown
Page : 38 pages
File Size : 49,7 Mb
Release : 1951
Category : Aerofoils
ISBN : UOM:39015086495267
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.
Author : James W. Wiggins
Publisher : Unknown
Page : 54 pages
File Size : 40,5 Mb
Release : 1954
Category : Airplanes
ISBN : UOM:39015086490375
An investigation was performed in the Langley high-speed 7- by 10-foot tunnel in order to determine the rolling derivatives for swept-wing-body configurations at angles of attack from 0 degrees to 13 degrees and at high subsonic Mach numbers. The wings had sweep angles of 3.6 degrees, 32.6 degrees, 45 degrees, and 60 degrees at the quarter-chord line, an aspect ratio of 4, a taper ratio of 0.6, and an NACA 65A006 airfoil section parallel to the free stream. The results indicate a reduction in the damping-in-roll derivative at the higher test angles of attack. Of the wings tested, instability of the damping-in-roll derivative was experienced over the largest ranges of angle of attack and Mach number for the 32.6 sweptback wing.
Author : Robert E. Dannenberg
Publisher : Unknown
Page : 678 pages
File Size : 41,9 Mb
Release : 1950
Category : Aerodynamic load
ISBN : STANFORD:36105024796083
Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.
Author : Arvid L. Keith,Jack Schiff
Publisher : Unknown
Page : 65 pages
File Size : 49,5 Mb
Release : 1955
Category : Airplanes
ISBN : OCLC:673500262
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. Installation of the wing-root inlet was accomplished with no significant effects on the force characteristics of the basic wing. The fuselage boundary layer entering the inlet was thin and required no boundary-layer-control device ahead of the inlet. Near unity inlet total-pressure recovery was obtained to about 86 percent of the maximum lift coefficient over a large range of inlet-velocity ratio. Maximum local velocities over the external surfaces of the inlet sections were no greater than those over the wing at a midspan station for the assumed high-speed operating conditions.
Author : Earl D. Knechtel
Publisher : Unknown
Page : 32 pages
File Size : 49,9 Mb
Release : 1957
Category : Airplanes
ISBN : UOM:39015086429803
An investigation was conducted to determine the effects of wing-tip droop on the longitudinal stability characteristics of a 53 and a 63 degree sweptback wing-body combination. Both models were tested with flat and abruptly drooped wing tips. The 63 degree wing was also tested with a curved drooped tip. In addition, the combined effects of wing fences and extended leading-edge flaps were investigated. The results showed that abrupt droop of the outer 40 percent of the basic 53 degree wing improved the stability characteristics of the model. For the 63 degree swept wing, curved droop caused slight beneficial effects on the stability, whereas abrupt droop caused adverse effects. In general, the most favorable stability characteristics were obtained for either flat or abruptly drooped wings with fences and extended leading-edge flaps.
Author : James W. Wiggins,Richard E. Kuhn
Publisher : Unknown
Page : 32 pages
File Size : 53,9 Mb
Release : 1954
Category : Aerodynamic load
ISBN : UOM:39015086490359
Author : Kenneth P. Spreemann
Publisher : Unknown
Page : 644 pages
File Size : 52,5 Mb
Release : 1957
Category : Airplanes
ISBN : STANFORD:36105024832128
This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.
Author : Albert P. Martina
Publisher : Unknown
Page : 38 pages
File Size : 48,8 Mb
Release : 1956
Category : Airplanes
ISBN : UOM:39015086466045
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.
Author : Macon C. Ellis,Lowell E. Hasel
Publisher : Unknown
Page : 44 pages
File Size : 43,5 Mb
Release : 1949
Category : Aerodynamic, Supersonic
ISBN : UOM:39015086494336
Results from a supersonic wind-tunnel investigation of a series of thin triangular and sweptback wings are presented. The triangular wing series consisted of eight triangular wings of vertex angles such that a range of leading-edge postions both inside and outside the Mach cone at the test Mach numbers of 1.43 and 1.71 was obtained. The three swept wings had angles of sweep at 45, 55, and 63 degrees and were tested at a Mach number of 1.43.
Author : Carl Joseph Wenzinger,Charles Frederick Marvin,Charles Horton Zimmerman,Ernest Franklin Fiock,John Bevill Peterson,John Brooks Wheatley,Maurice John Brevoort,Robert Cecil Platt,United States. National Advisory Committee for Aeronautics,Carl Henry Roeder,Armistead Wharton,Carlton Bioletti,Clyde Wendell Smith,Vern Gordon Rollin
Publisher : Unknown
Page : 176 pages
File Size : 46,7 Mb
Release : 1936
Category : Aerofoils
ISBN : OSU:32435063882229