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Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 And Naca 65a006 Airfoil Section 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 Aerodynamic Characteristics Of A Wing With Quarter Chord Line Swept Back 35 Aspect Ratio 6 Taper Ratio 0 6 And Naca 65a006 Airfoil Section book. This book definitely worth reading, it is an incredibly well-written.
Author : William C. Sleeman
Publisher : Unknown
Page : 36 pages
File Size : 53,6 Mb
Release : 1949
Category : Aerodynamics, Transonic
ISBN : UOM:39015086464610
Author : Boyd C. Myers
Publisher : Unknown
Page : 36 pages
File Size : 48,7 Mb
Release : 1949
Category : Airplane
ISBN : UOM:39015086490524
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.
Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 242 pages
File Size : 55,9 Mb
Release : 1955
Category : Aeronautics
ISBN : STANFORD:36105024165651
Author : Anonim
Publisher : Unknown
Page : 750 pages
File Size : 48,5 Mb
Release : 1949
Category : Aeronautics
ISBN : UVA:X004173285
Author : Robert F. Thompson
Publisher : Unknown
Page : 28 pages
File Size : 54,6 Mb
Release : 1950
Category : Aerofoils
ISBN : UOM:39015086490557
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.
Author : William C. Sleeman
Publisher : Unknown
Page : 34 pages
File Size : 49,6 Mb
Release : 1949
Category : Aerofoils
ISBN : UOM:39015086464503
This paper presents the results of the investigation of wing-alone and wing-fuselage combination employing a delta wing having 45 degree sweepback of the leading edge, aspect ratio 4, 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 also were obtained for these configurations, and are presented for a range of tail heights at one tail length. In order to expedite publishing of these data, only a brief analysis is included.
Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 508 pages
File Size : 50,6 Mb
Release : 1954
Category : Aeronautics
ISBN : IND:30000098603164
Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 442 pages
File Size : 44,7 Mb
Release : 2024-07-04
Category : Aeronautics
ISBN : OSU:32435062280326
Author : Anonim
Publisher : Unknown
Page : 524 pages
File Size : 55,8 Mb
Release : 1949
Category : Electronic
ISBN : NASA:31769000528763
Author : Anonim
Publisher : Unknown
Page : 904 pages
File Size : 49,5 Mb
Release : 1958
Category : Electronic
ISBN : CUB:U183040598792
Author : Anonim
Publisher : Unknown
Page : 1212 pages
File Size : 55,8 Mb
Release : 1954
Category : Aeronautics
ISBN : UOM:39015024394291
Author : Douglas R. Lord
Publisher : Unknown
Page : 52 pages
File Size : 41,7 Mb
Release : 1957
Category : Aerodynamics
ISBN : UOM:39015086466151
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.
Author : Edward J. Hopkins
Publisher : Unknown
Page : 40 pages
File Size : 55,9 Mb
Release : 1951
Category : Aerodynamic load
ISBN : UOM:39015086495051
Lift, pitching-moment, and pressure distribution were measured on a wing which was swept -40, -30, 0, 35, and 45 degrees. The wing span was decreased to give aspect ratios 6.8, 5.3, 4.2, 3.4, and 2.8. The effects of independent variations of sweep and aspect ratio on the lift, pitching-moment, and span-load characteristics of the wings are compared with the effects estimated by use of the Weissinger method.
Author : M. Leroy Spearman
Publisher : Unknown
Page : 34 pages
File Size : 41,7 Mb
Release : 1957
Category : Airplanes
ISBN : UOM:39015086466235
An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the effects of wing and horizontal-tail vertical location on the aerodynamic characteristics in sideslip at various angles of attack for a supersonic airplane configuration at Mach numbers of 1.41 and 2.01. The basic model was equipped with a wing and horizontal tail, each having 45 degree sweep and an aspect ratio of 4. The wing had a taper ratio of 0.2 and NACA 65A004 sections; the horizontal tail had a taper ratio of 0.4 and NACA 65A006 sections.
Author : Jack F. Runckel
Publisher : Unknown
Page : 104 pages
File Size : 51,9 Mb
Release : 1956
Category : Aerodynamic load
ISBN : UOM:39015095100999
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.