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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
- 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
- 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
- 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
- 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
- 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
- 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
- Some Factors Affecting the Stability and Performance Characteristics of Canard Aircraft Configurations
- Effects of Canard Surface Size on Stability and Control Characteristics of Two Canard Airplane Configuration at Mach Numbers of 1.41 and 2.01
- 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