TRAIL - Technical Report Archive and Image Library

Hinge Moment and Effectiveness of an Unswept Constant-Chord Control and an Overhang-Balanced, Swept Hinge-Line Control on an 80 Degree Swept Pointed Wing at Mach Numbers from 0.75 to 1.96

Failure Characteristics of Pressurized Stiffened Cylinders

Performance of a Double-Ramp Side Inlet With Combinations of Fuselage, Ramp, and Throat Boundary-Layer Removal, Mach Number Range, 1.5 to 2.0

Performance of Pentaborane, Pentaborane - JP-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-scale Turbojet Engine

Performance of Several Half-Conical Side Inlets at Supersonic and Subsonic Speeds

Performance of Variable Two-Dimensional Inlet Designed for Engine-Inlet Matching 1 - Performance at Design Mach Number of 3.07

Some Effects of Roll Rate on the Longitudinal Stability Characteristics of a Cruciform Missile Configuration as Determined From Flight Test for a Mach Number Range of 1.1 to 1.8

Some Transonic Aerodynamic Characteristics of a Model Similar to the McDonnell F3H-2N Airplane

Static Lateral and Directional Stability and Control Characteristics of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01

Preliminary Report on Experimental Investigation of Engine Dynamics and Controls for a 48-Inch Ramjet Engine

Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 1/20-Scale Model of the McDonnell F4H-1 Airplane at Mach Numbers of 1.59, 1.89, and 2.09

Surge-Inception Study in a Two-Spool Turbojet Engine

Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane

Static Longitudinal and Lateral Stability Characteristics Including Effects of Transonic Area Rule and Wing Modification of a 0.10- Scale Model of the Douglas A4D-1 Airplane at Transonic Speeds

Some Flight Data for the Chance Vought Regulus 2 Missile

Wind Tunnel Investigation at High Subsonic Speeds of Drag at 0 Degrees Angle of Attack of Swept-Wing Fuselage Models With Pylon Mounted and Semisubmerged Missiles

Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1

An Airborne Simulator Investigation of the Accuracy of an Optical Track Command Missile Guidance System

Tests With Hydrogen Fuel in a Simulated Afterburner

Thermal Stability of Decaborane and of a Commercial Ethyl Decaborane (HEF-3) in the Range 202 Degrees to 252 Degrees C

An Oil-Stream Photomicrographic Aeroscope for Obtaining Cloud Liquid-Water Content and Droplet Size Distributions in Flight

Experimental Droplet Impingement on Several Two-Dimensional Airfoils with Thickness Ratios of 6 to 16 Percent

Drag at Model Trim Lift of a 1/15-Scale Convair B-58 Supersonic Bomber

Low-Speed Investigation of the Effect of Small Canard Surfaces on the Directional Stability of a Sweptback-Wing Fighter-Airplane Model

Full-Scale Evaluation of Some Flameholder Design Concepts for High-Inlet-Velocity Afterburners

Pressure Distributions and Aerodynamic Characteristics of Several Spoiler-type Controls on a Trapezoidal Wing at Mach Numbers of 1.61 and 2.01

Presentation on Facility Problems in High-Temperature Structures Research

Effect of Combustion Gas Properties on Turbojet-Engine Performance With Hydrogen as Fuel

Experimental Investigation of a High Subsonic Mach Number Turbine Having High Rotor Blade Suction-Surface Diffusion

Force and Pressure-Distribution Investigation to High Angles of Attack on All-Movable Triangular and Rectangular Wings in Combination With a Body at Supersonic Speeds

Full-Scale Wind-Tunnel Tests of a 35 Degree Swept-Wing Fighter Airplane With a Spoiler-Slot-Deflector Lateral Control System

The Origin and Distribution of Supsonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5 - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number, 2.01

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 6. - Swept-Wing Heavy-Bomber Configuration With Stores of Different Sizes and Shapes

Low-Speed Roll Effectiveness of a Differentially Deflected Horizontal-Tail Surface on a 42 Degree Swept-Wing Model

Minimum Drag of Four Versions of a Swept-Wing Fighter Airplane Obtained From Flight Tests of Rocket-Boosted Models at Mach Numbers From 0.81 to 1.71

Performance at Simulated High Altitudes of a Prevaporizing Annular Turbojet Combustor Having Low Pressure Loss

Performance of a Short Turbojet Combustor With Hydrogen Fuel in a Quarter-Annulus Duct and Comparison With Performance in a Full-Scale Engine

Transonic Aerodynamic and Trim Characteristics of a Multi-Engine Delta-Wing Airplane Model

Compilation and Analysis of U.S. Turbojet and Ram-Jet Engine Characteristics

Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96

Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96

Afterburner Performance With Combustion-Chamber Lengths From 10 to 62 Inches at Several Afterburner-Inlet Temperatures

Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds

The Appearance of a Boric Oxide Exhaust Cloud From a Turbojet Engine Operating on Trimethylborate Fuel

Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53

Longitudinal Aerodynamic Characteristics of Various Configurations of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01

An Investigation of the Afterbody Pressure Distribution and Fin Loading Characteristics of a Specialized Store Configuration at Transonic Speeds

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