Effects Of Wing Tip Droop On The Longitudinal Characteristics Of Two Highly Swept Wing Body Combinations At Mach Numbers From 0 6 To 1 4

Author : Earl D. Knechtel
Publisher : Unknown
Page : 32 pages
File Size : 50,8 Mb
Release : 1957
Category : Airplanes
ISBN : UOM:39015086429803

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Effects of Wing-tip Droop on the Longitudinal Characteristics of Two Highly Swept Wing-body Combinations at Mach Numbers from 0.6 to 1.4 by Earl D. Knechtel Pdf

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 : United States. National Aeronautics and Space Administration
Publisher : Unknown
Page : 128 pages
File Size : 47,8 Mb
Release : 1960-07
Category : Electronic
ISBN : STANFORD:36105024165701

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Index to NASA Technical Publications by United States. National Aeronautics and Space Administration Pdf

Author : Charles F. Whitcomb
Publisher : Unknown
Page : 34 pages
File Size : 45,5 Mb
Release : 1956
Category : Aerodynamics, Transonic
ISBN : UOM:39015095100957

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Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches by Charles F. Whitcomb Pdf

An investigation of the effects of several wing leading-edge modifications on the aerodynamic characteristics of a 45 degree swept-wing fighter-airplane model has been conducted in the Langley 16-foot transonic tunnel at low and high lifting conditions at Mach numbers from 0.85 to 1.03. The investigation included the determination of the effect on longitudinal stability and performance characteristics of wing leading-edge and chord-extension droops of 6 and 20 degrees, chord-extension overhangs of 0.075c and 0.15c (where c is the wing chord), leading-edge notches cut out at the inboard end of the 0.075c chord-extension to depths of 0.075c and 0.125c, and indentation of the model fuselage to conform partially to the supersonic area rule for a Mach number of 1.20. Lift, drag, and pitching-moment data were obtained for configurations with the tail on and off. Comparisons of data obtained from the present model with data from a configuration with leading-edge slats are included.

Author : Arthur James Wells
Publisher : Unknown
Page : 1728 pages
File Size : 50,6 Mb
Release : 1960
Category : English literature
ISBN : UOM:39015079755081

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The British National Bibliography by Arthur James Wells Pdf

Author : Albert G. Few
Publisher : Unknown
Page : 78 pages
File Size : 41,7 Mb
Release : 1954
Category : Airplanes
ISBN : UOM:39015086490151

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Some Effects of Tail Height and Wing Plan Form on the Static Longitudinal Stability Characteristics of a Small-scale Model at High Subsonic Speeds by Albert G. Few Pdf

The drag due to lift increases with increasing sweep through the Mach number range. Some increase in bag due to lift is evident decrease in taper ratio for wings having 300of sweep through most of the speed range.

Author : John A. Axelson,J. Conrad Crown
Publisher : Unknown
Page : 20 pages
File Size : 53,5 Mb
Release : 1948
Category : Aeronautics
ISBN : UOM:39015086432724

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An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence by John A. Axelson,J. Conrad Crown Pdf

An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability.

Author : Charles F. Whitcomb,Harry T. Norton
Publisher : Unknown
Page : 30 pages
File Size : 42,6 Mb
Release : 1961
Category : Aerodynamics, aircraft
ISBN : OCLC:227262195

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Transonic Investigation of Aerodynamic Characteristics of a Swept-wing Fighter-airplane Model with Leading-edge Droop in Combination with Outboard Chord-extensions and Notches by Charles F. Whitcomb,Harry T. Norton Pdf

Author : Anonim
Publisher : Unknown
Page : 48 pages
File Size : 49,8 Mb
Release : 1960
Category : Electronic
ISBN : NASA:31769000460470

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The Effects of Wing-tip Droop on the Aerodynamic Characteristics of a Delta-wing Aircraft at Supersonic Speeds by Anonim Pdf

Author : Harry W. Carlson,John P. Gapcynski
Publisher : Unknown
Page : 36 pages
File Size : 42,5 Mb
Release : 1955
Category : Aerodynamics
ISBN : UFL:31262081065954

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An Experimental Investigation at a Mach Number of 2.01 of the Effects of Body Cross-section Shape on the Aerodynamic Characteristics of Bodies and Wing-body Combinations by Harry W. Carlson,John P. Gapcynski Pdf

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 : William E. Palmer,Dale L. Burrows
Publisher : Unknown
Page : 36 pages
File Size : 54,7 Mb
Release : 1955
Category : Delta wing airplanes
ISBN : UOM:39015095100866

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A Transonic Wind-tunnel Investigation of the Longitudinal Force and Moment Characteristics of Two Delta Wings and One Clipped-tip Delta Wing of 4 Percent Thickness on a Slender Body by William E. Palmer,Dale L. Burrows Pdf

Author : Marlowe D. Cassetti,Richard J. Re,William B. Igoe
Publisher : Unknown
Page : 104 pages
File Size : 41,5 Mb
Release : 1961
Category : Transonic wind tunnels
ISBN : UIUC:30112106914986

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Transonic Aerodynamic Loading Characteristics of a Wing-body-tail Combination Having 52.5° Sweptback Wing of Aspect Ratio 3 with Conical Wing Camber and Body Indentation for a Design Mach Number [square Root Of] 2 by Marlowe D. Cassetti,Richard J. Re,William B. Igoe Pdf

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.

Author : Royce L. McKinney,Lloyd S. Jernell
Publisher : Unknown
Page : 52 pages
File Size : 50,8 Mb
Release : 1965
Category : Aerodynamic load
ISBN : UIUC:30112104504136

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Effects of Wing Planform on the Aerodynamic Characteristics of a Wing-body-tail Model at Mach Numbers 1.57, 2.16, and 2.87 by Royce L. McKinney,Lloyd S. Jernell Pdf

Author : Anonim
Publisher : Unknown
Page : 32 pages
File Size : 55,5 Mb
Release : 1961
Category : Electronic
ISBN : NASA:31769000461759

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Static Longitudinal and Lateral Aerodynamic Characteristics at a Mach Number of 2.20 of a V/STOL Airplane Configuration with a Variable-sweep Wing and with a Skewed Wing Design by Anonim Pdf

Author : Anonim
Publisher : Unknown
Page : 32 pages
File Size : 45,9 Mb
Release : 1961
Category : Electronic
ISBN : NASA:31769000462005

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Effects of Wing Section and Body Vertical Location on the Longitudinal Aerodynamic Characteristics at Mach Number 4.63 of a Configuration Having a 70 Deg Delta Wing and a Low Volume Body by Anonim Pdf

Author : Robert H. Neely,Roland F. Griner
Publisher : Unknown
Page : 100 pages
File Size : 43,6 Mb
Release : 1959
Category : Aeronautics
ISBN : NASA:31769000420995

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Summary and Analysis of Horizontal-tail Contribution to Longitudinal Stability of Swept-wing Airplanes at Low Speeds by Robert H. Neely,Roland F. Griner Pdf

Air-flow characteristics behind wings and wing-body combinations are described and are related to the downwash at specific tail locations for unseparated and separated flow conditions. The effects of various parameters and control devices on the air-flow characteristics and tail contribution are analyzed and demonstrated. An attempt has been made to summarize certain data in a form useful for design. The experimental data herein were obtained mostly at Reynolds numbers greater than 4 x 105 and at Mach numbers less than 0.25.