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Wind Tunnel Investigation of Control-Surface Characteristics 23: A 0.25-Airfoil-Chord Flap With Tab Having a Chord Twice the Flap Chord on an NACA 0009 Airfoil

Preliminary investigation at low speed of downwash characteristics of small-scale sweptback wings

The effect of negative dihedral, tip droop, and wing-tip shape on the low-speed aerodynamic characteristics of a complete model having a 45 degrees sweptback wing

Wind-Tunnel Investigation of an NACA 0009 Airfoil With 0.25-and 0.50-Airfoil-Chord Plain Flaps Tested Independently and in Combination

An Investigation of the Low-Speed Static Stability Characteristics of Complete Models Having Sweptback and Sweptforward Wings

Longitudinal Stability and Control Characteristics at Transonic Speeds of a Semispan Airplane Model Having a 45 Degree Sweptback Wing and Tail as Obtained by the Transonic-Bump Method

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback: Static longitudinal stability and control characteristics at a Mach number of 1.59

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : static lateral stability characteristics at Mach numbers of 1.40 and 1.59

An investigation at Mach numbers of 1.40 and 1.59 of the effects of aileron profile on the aerodynamic characteristics of a complete model of a supersonic aircraft configuration

Wind-tunnel investigation of a ram-jet canard missile model having a wing and canard surfaces of delta plan form with 70 degree swept leading edges : longitudinal and lateral stability and control characteristics at a Mach number of 1.60

The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Component tests to determine the aerodynamic characteristics of an all-moveable 70 degree delta canard-type control in the presence of a body at a Mach number of 1.61

Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01

Static Longitudinal Stability and Control Characteristics of a 1/16 -Scale Model of the Douglas D-558-II Research Airplane at Mach Numbers of 1.61 and 2.01

Effect of Large Deflection of a Canard Control and Deflections of a Wing-Tip Control on the Static-Stability and Induced-Roll Characteristics of a Cruciform Canard Missile at a Mach Number of 2.01

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : aerodynamic characteristics of the configuration equipped with a canard control surface at a Mach number of 1.89

Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41

Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls

Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Pitch and Sideslip of Some Canard-Type Missiles Having Cruciform Wings and Canard Surfaces With 70 Degree Delta Plan Forms

Investigation of aerodynamic characteristics in pitch and sideslip of a 45 degree sweptback-wing airplane model with various vertical locations of wing and horizontal tail : basic-data presentation, M = 2.01

Investigation of the aerodynamic characteristics in pitch and sideslip of a 45 degree sweptback-wing airplane model with various vertical locations of the wing and horizontal tail : effect of wing location and geometric dihedral for the wing-body com

Aerodynamic characteristics of various configurations of a model of a 45 degree swept-wing airplane at a Mach number of 2.01

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Mach Numbers of 1.41, 1.61, and 2.01

Longitudinal and Lateral Stability, Control Characteristics, and Vertical-Tail-Load Measurements for 0.03-Scale Model of the Avro CF-105 Airplane at Mach Number 1.41

Investigation of aerodynamic characteristics in pitch and sideslip of a 45 degree sweptback-wing airplane model with various vertical locations of wing and horizontal tail : static longitudinal stability and control, M = 2.01

Longitudinal and lateral stability characteristics of a low-aspect-ratio unswept-wing airplane model at Mach numbers of 1.82 and 2.01

The Effects of the Addition of Small Fuselage-Mounted Fins on the Static Directional Stability Characteristics of a Model of a 45 Degree Swept-Wing Airplane at Angles of Attack up to 15.3 degrees at a Mach Number of 2.01

Limited Investigation of Effects of Differential Horizontal-Tail Deflection on Lateral Control Characteristics of Two Swept-Wing Airplane Models at Mach Numbers From 1.4 to 2.0

Static lateral stability and control characteristics of a model of a 45 degree swept-wing fighter airplane with various vertical tails at Mach numbers of 1.41, 1.61, and 2.01

Longitudinal and Lateral Stability Characteristics of a 0.04-Scale Model of the Lockheed F-104A Airplane at Mach Numbers of 1.82 and 2.01. Coord. No. AF-245

Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations

Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations

Longitudinal stability and control characteristics at Mach numbers of 1.41 and 2.01 of a 67 degree swept-wing airplane configuration with canard control surfaces

Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01

Effects of Canard Surface Size on Stability and Control Characteristics of Two Canard Airplane Configuration at Mach Numbers of 1.41 and 2.01

Some Factors Affecting the Stability and Performance Characteristics of Canard Aircraft Configurations

Longitudinal and Lateral Stability and Control Characteristics at Mach Number 2.01 of a 60 Degree Delta-Wing Airplane Configuration Equipped With a Canard Control and With Wing Trailing-Edge Flap Controls


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