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A Tabulation Of Section Aerodynamic Characteristics At Mach Numbers Of 1 61 And 2 01 For Four Swept Wings Having The Same Planform But Different Surface Shapes 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 A Tabulation Of Section Aerodynamic Characteristics At Mach Numbers Of 1 61 And 2 01 For Four Swept Wings Having The Same Planform But Different Surface Shapes book. This book definitely worth reading, it is an incredibly well-written.
Author : Anonim
Publisher : Unknown
Page : 914 pages
File Size : 47,8 Mb
Release : 1962
Category : Aeronautics
ISBN : UCSD:31822015403520
Author : Emma Jean Landrum
Publisher : Unknown
Page : 76 pages
File Size : 54,7 Mb
Release : 1962
Category : Aerodynamics
ISBN : UIUC:30112106873349
Author : United States. Department of Commerce. Office of Technical Services
Publisher : Unknown
Page : 1222 pages
File Size : 45,5 Mb
Release : 1962-06
Category : Government publications
ISBN : UOM:39015057256318
Author : John A. Kelly
Publisher : Unknown
Page : 56 pages
File Size : 40,5 Mb
Release : 1951
Category : Aerodynamic load
ISBN : UOM:39015086489971
The data presented in this report were obtained by North American Aviation, Inc., from an investigation conducted in the Southern California Cooperative Wind Tunnel. Tests were made over a range of Mach numbers from 0.300 to 0.883 to determine the aerodynamic characteristics of a semispan model of a 35 degree swept-back wing equipped with a leading-edge slat and to gain additional knowledge of the aerodynamic loads and automatic operation of the slat. Lift, drag, and pitching-moment characteristics of a model wing in the presence of a fuselage were measured as well as pressures acting on the slat in the retracted and the full-open positions. The pressure data were analyzed to ascertain the opening characteristics of the slat for two possible circular-arc slat tracks which could be used for automatic operation of the slat.
Author : William C. Sleeman
Publisher : Unknown
Page : 34 pages
File Size : 47,8 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 : Anonim
Publisher : Unknown
Page : 42 pages
File Size : 51,8 Mb
Release : 1959
Category : Electronic
ISBN : NASA:31769000457401
Author : Anonim
Publisher : Unknown
Page : 44 pages
File Size : 43,8 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000458862
Author : Harry W. Carlson,John P. Gapcynski
Publisher : Unknown
Page : 36 pages
File Size : 54,6 Mb
Release : 1955
Category : Aerodynamics
ISBN : UFL:31262081065954
Abstract: An experimental investigation has been performed to determine the effect of changes in body cross-section shape on the aerodynamic characteristics of bodies and wing-body combinations. A series of 13 bodies having a given length and given longitudinal distribution of cross-sectional area but various cross-section shapes were tested at a Mach number of 2.01. The bodies were tested alone and in combination with a 47° sweptback wing having a 6-percent-thick hexagonal section.
Author : Ralph P. Bielat
Publisher : Unknown
Page : 44 pages
File Size : 53,7 Mb
Release : 1951
Category : Aerodynamics, Transonic
ISBN : UOM:39015086506873
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.
Author : M. Leroy Spearman
Publisher : Unknown
Page : 34 pages
File Size : 45,6 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 : Edward J. Hopkins,Raymond M. Hicks,Ralph L. Carmichael
Publisher : Unknown
Page : 98 pages
File Size : 40,9 Mb
Release : 1967
Category : Airplanes
ISBN : UIUC:30112106686998
Author : A. Warner Robins,Roy V. Harris,Charlie M. Jackson
Publisher : Unknown
Page : 30 pages
File Size : 53,7 Mb
Release : 1960
Category : Electronic
ISBN : UIUC:30112106773671
Author : Samuel M. Dollyhigh
Publisher : Unknown
Page : 126 pages
File Size : 50,9 Mb
Release : 1971
Category : Aerodynamics
ISBN : UIUC:30112106693176
An experimental investigation was made in the Mach number range from 1.60 to 2.86 to determine the static longitudinal aerodynamic characteristics of close-coupled wing-canard configurations. Three canards, ranging in exposed planform area from 17.5 to 30.0 percent of the wing reference area, were employed in this investigation. The canards were either located in the plane of the wing or in a position 18.5 percent of the wing mean geometric chord above the wing plane. Most data obtained were for a model with a 60 deg leading-edge-sweep wing; however, a small amount of data were obtained for a 44 deg leading-edge-sweep wing. The model utilized two balances to isolate interference effects between wing and canard. In general, it was determined that at angle of attack for all configurations investigated with the canard in the plane of the wing an unfavorable interference exists which causes the additional lift on the canard generated by a canard deflection to be lost on the wing due to an increased downwash at the wing from the canard. Further, this interference decreased somewhat with increasing Mach number. Raising the canard above the plane of the wing also greatly decreased the interference of the canard deflection on the wing lift. However, at Mach 2.86 the presence of the canard in the high position had a greater unfavorable interference effect at high angles of attack than the canard in the wing plane. This interference resulted in the in-plane canard having better trimmed performance at Mach 2.86 for the same center-of-gravity location.
Author : Douglas R. Lord
Publisher : Unknown
Page : 52 pages
File Size : 48,7 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 : Marlowe D. Cassetti,Richard J. Re,William B. Igoe
Publisher : Unknown
Page : 104 pages
File Size : 42,6 Mb
Release : 1961
Category : Transonic wind tunnels
ISBN : UIUC:30112106914986
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.