Browse TRAIL Inventories

Flight Tests of a Man Standing on a Platform Supported by a Teetering Rotor

Investigation at Transonic Speeds of the Lateral-Control and Hinge-Moment Characteristics of a Flap-Type Spoiler Aileron on a 60 Degree Delta Wing

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Stability and Control Characteristics at a Mach Number of 1.61 of the Complete Configuration Equipped With Spoilers

Investigation of a Pulse-Jet-Powered Helicopter Rotor on the Langley Helicopter Test Tower

An Investigation of a Method for Obtaining Hydrodynamic Data at Very High Speeds With a Free Water Jet

Investigation of a Canard Missile Configuration (NACA RM-4) in the Langley 9-Inch Supersonic Tunnel at Mach Numbers of 1.62 and 1.93

Bibliography of NACA Reports Related to Aircraft Control and Guidance Systems January 1949 - April 1954

Preliminary Flight Measurements of the Total-Pressure Recovery of a Split-Wing Ram-Jet Inlet at Mach Numbers From 1.4 to 3.16

Development of Metal-Bonding Adhesives With Improved Heat-Resistant Properties

Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section

Additional Static and Fatigue Tests of High-Strength Aluminum-Alloy Bolted Joints

Aerodynamic loads on a leading-edge flap and a leading-edge slat on the NACA 64A010 airfoil section

Aerodynamic investigation of a four-blade propeller operating through an angle-of-attack range from 0 to 180 degrees

Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section

Aerodynamics of slender wings and wing-body combinations having swept trailing edges

Aerodynamic characteristics of the NACA 64-010 and 0010-1.10 40/1.051 airfoil sections at Mach numbers from 0.30 to 0.85 and Reynolds numbers from 4.0 x 10(exp. 6) to 8.0 x 10(exp. 6)

Airfoil section characteristics at high angles of attack

The Ames 10- by 14-Inch Supersonic Wind Tunnel

Aerodynamic Characteristics at High and Low Subsonic Mach Numbers of the NACA 0012, 64₂-015, and 64₃-018 Airfoil Sections at Angles of Attack from -2 Degrees to 30 Degrees

Drop Hammer Tests With Three Oleo Strut Models and Three Different Shock Strut Oils at Low Temperatures

Effect of Rocket-Motor Operation on the Drag of Three 1/5-Scale Hermes A-3A Models in Free Flight

Photographic Study of Rotary Screaming and Other Oscillations in a Rocket Engine

Performance Characteristics of Several Full-Scale Double-Shroud Ejector Configurations Over a Range of Primary Gas Temperatures

A Preliminary Investigation of the Pressure Recovery of Several Two-Dimensional Supersonic Inlets at Mach Number of 2.01

Preliminary Investigation of the Performance of a Single Tubular Combustor at Pressure Up to 12 Atmospheres

A Preliminary Flight Investigation of an Oil-Flow Technique for Air-Flow Visualization

Experimental Investigation of the Damping in Roll of Cruciform Triangular Wing-Body Combinations at Mach Numbers From 1.5 to 6.0

Exploratory Investigation of External Stores in the Aerodynamic Characteristics of a 1/16-Scale Model of the Douglas D-558-II Research Airplane at a Mach Number of 2.01

Experimental Investigation of the Oscillating Forces and Moments on a Two-Dimensional Wing Equipped With an Oscillating Circular-Arc Spoiler

Flight and Preflight Evaluation of an Automatic Thrust-Coefficient Control System in a Twin-Engine Ram-Jet Missile

Flight-Determined Pressure Measurements Over the Wing of the Douglas D-558-II Research Airplane at Mach Numbers Up to 1.14

Experimental Investigation of Rotating Stall and Blade Vibration in the Axial-Flow Compressor of a Turbojet Engine

Flight Determination of the Buffeting Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback

Stabilization of 50-Percent Magnesium - JP-4 Slurries With Some Aluminum Soaps of C(Sub 8) Acids

Preliminary Report of Experimental Investigation of Ram-Jet Controls and Engine Dynamics

Preliminary Investigation of the Flow in an Annular-Diffuser-Tailpipe Combination With an Abrupt Area Expansion and Suction, Injection, and Vortex-Generator Flow Controls

Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbine for Turbojet Engines 1: Turbine Performance and Engine Weight-Flow Capacity

Application of Radial-Equilibrium Condition to Axial-Flow Turbomachine Design Including Consideration of Change of Entropy With Radius Downstream of Blade Row

Experimental Sea-Level Static Investigation of a Short Afterburner

Transonic Aerodynamic and Loads Characteristics of a 4-Percent-Thick Unswept-Wing--Fuselage Combination

The Effect of Nacelle Location on the Zero-Lift Drags of 45 Degree Sweptback Wing-Body Configurations Having Boattail and Cylindrical Afterbodies as Determined by Flight Tests at Transonic Speeds

A Transonic Wind-Tunnel Investigation of the Longitudinal Force and Moment Characteristics of a Plane and a Cambered 3-Percent-Thick Delta Wing of Aspect Ratio 3 on a Slender Body

A Transonic Wind-Tunnel Investigation of the Static Lateral, Directional, and Longitudinal Stability Characteristics of the Martin B-61A Missile (Matador)

Transonic Flight Test of a Rocket-Powered Model to Determine Propulsive Jet Influence on the Configuration Drag

Transonic Drag Measurements of Eight Body-Nose Shapes

A Study of the Problem of Designing Airplanes With Satisfactory Inherent Damping of the Dutch Roll Oscillation

Rocket-powered-model investigation of the hinge-moment and normal-force characteristics of a half-diamond tip control on a 60 degree sweptback diamond wind between Mach numbers of 0.5 and 1.3

Rocket-Powered Model Investigation of Lift, Drag, and Stability of a Body-Tail Configuration at Mach Numbers From 0.8 to 2.3 and Angles of Attack Between Plus or Minus 6.5 Degrees

Pressure Distributions on Plug- and Semaphore-Type Spoiler Ailerons on a 35 Degree Sweptback Wing of Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section at High Subsonic Speeds

Pressures and Associated Aerodynamic and Load Characteristics for Two Bodies of Revolution at Transonic Speeds


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