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The Effect Of A Change In Airfoil Section On The Hinge Moment Characteristics Of A Half Delta Tip Control With A 60 Sweep Angle At A Mach Number Of 6 9 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 The Effect Of A Change In Airfoil Section On The Hinge Moment Characteristics Of A Half Delta Tip Control With A 60 Sweep Angle At A Mach Number Of 6 9 book. This book definitely worth reading, it is an incredibly well-written.
Author : David E. Fetterman,Herbert W. Ridyard
Publisher : Unknown
Page : 18 pages
File Size : 47,6 Mb
Release : 1954
Category : Aerofoils
ISBN : UOM:39015086465674
Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 442 pages
File Size : 52,6 Mb
Release : 2024-06-01
Category : Aeronautics
ISBN : OSU:32435062280326
Author : United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 508 pages
File Size : 40,5 Mb
Release : 1954
Category : Aeronautics
ISBN : IND:30000098603164
Author : Odell A. Morris
Publisher : Unknown
Page : 38 pages
File Size : 49,7 Mb
Release : 1953
Category : Airplanes
ISBN : UOM:39015095100726
Author : Lawrence Duncan Guy,Hoyt V. Brown
Publisher : Unknown
Page : 42 pages
File Size : 51,6 Mb
Release : 1955
Category : Airplanes
ISBN : UOM:39015086506998
Author : Lawrence D. Guy
Publisher : Unknown
Page : 52 pages
File Size : 50,5 Mb
Release : 1954
Category : Aerodynamics, Supersonic
ISBN : UOM:39015095100817
A wind-tunnel investigation has been made of two unswept, partial-span, flap-type controls (differing only in hinge-line location) mounted on a 60 degree delta wing. One control was unbalanced and the other has a 100-percent overhang balance. Control hinge moments as well as aerodynamic characteristics of the complete wing-body combination were obtained for control deflections from 0 to 40 degrees over an angle-of-attack range of plus or minus 12 degrees at Mach numbers from 0.75 to 1.96. Reynolds numbers varied between 2,200,000 and 2,200,000. Expressions derived from linear theory for the hinge-moment coefficient due to angle of attack for unswept partial-span controls (which extend neither to the wing tip nor to the wing center line) on triangular wings having subsonic leading edges are given in an appendix.
Author : Paul E. Purser,Charles B. Cook
Publisher : Unknown
Page : 34 pages
File Size : 45,7 Mb
Release : 1947
Category : Aerofoils
ISBN : UOM:39015095016161
Various wind-tunnel data on the hinge-moment characteristics of control-surface tabs have been collected and analyzed. The data, all of which are for plain unbalanced tabs, were obtained from force tests of models in two- and three-dimensional flow and from pressure-distribution measurements on models in two-dimensional flow. Some data that show the effects of Mach number on tab hinge moments for representative conventional and NACA 6-series airfoil sections are presented.
Author : K. R. Czarnecki,Douglas R. Lord
Publisher : Unknown
Page : 124 pages
File Size : 54,7 Mb
Release : 1959
Category : Aerodynamic load
ISBN : UIUC:30112104457996
Author : William C. Sleeman
Publisher : Unknown
Page : 34 pages
File Size : 49,7 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 : Lawrence Duncan Guy,United States. National Advisory Committee for Aeronautics
Publisher : Unknown
Page : 54 pages
File Size : 52,8 Mb
Release : 1957
Category : Airplanes
ISBN : OCLC:696348044
Author : Douglas R. Lord
Publisher : Unknown
Page : 52 pages
File Size : 51,8 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 : Anonim
Publisher : Unknown
Page : 128 pages
File Size : 51,5 Mb
Release : 1959
Category : Electronic
ISBN : NASA:31769000457799
Author : W. F. Lindsey
Publisher : Unknown
Page : 94 pages
File Size : 54,6 Mb
Release : 1946
Category : Aerodynamic load
ISBN : UFL:31262081050048
An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at 0.20 flap deflections from 0 to -12 degree. Test data were obtained for Mach numbers from 0.28 to approximately 0.74. The results show that the effectiveness of the trailing-edge-type control surface rapidly decreased and approached zero as the Mach number increased above the critical value.
Author : George C. Ashby
Publisher : Unknown
Page : 28 pages
File Size : 45,7 Mb
Release : 1972
Category : Mach number
ISBN : UIUC:30112106882977
Elevon hinge moments were determined from measured surface pressures on a typical delta-wing shuttle orbiter model at selective deflection angles for comparison with the extensive experimental and analytical hinge-moment data previously reported for a simple 75 [degrees] delta wing with a trailing-edge control. The angles of attack were from 0 [degrees] to 55 [degrees] at elevondeflection angles of -45.5 [degrees], O [degrees], and 20°. The results show that the elevon hinge moments on the shuttle orbiter are essentially the same as those measured earlier for the more basic model. Also included is an appendix describing a cubic spline function technique used to determine the hinge moments from elevon surface-pressure measurements.
Author : William E. Palmer,Dale L. Burrows
Publisher : Unknown
Page : 36 pages
File Size : 55,8 Mb
Release : 1955
Category : Delta wing airplanes
ISBN : UOM:39015095100866