TRAIL - Technical Report Archive and Image Library

The Effects of Body Vortices and the Wing Shock-Expansion Field on the Pitch-Up Characteristics of Supersonic Airplanes

Correlations Among Ice Measurements, Impingement Rates Icing Conditions, and Drag Coefficients for Unswept NACA 65A004 Airfoil

Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area

Accelerations in Transport-Airplane Crashes

Studies of OH, CO, CH, and C₂ Radiation From Laminar and Turbulent Propane-Air and Ethylene-Air Flames

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

Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets

Investigation of an All-Moveable Control Surface at a Mach Number of 6.86 for Possible Flutter

A Flight Investigation of the Effects of Varied Lateral Damping on the Effectiveness of a Fighter Airplane as a Gun Platform

Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers From 1.90 to 3.07

High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser

Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65

Investigation of Vortex Movements About a Wing in Steady Subsonic Flow Undergoing a Large Angle-of-Attack Change in a Blast-Induced Gust

Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Simplified T-Tail Oscillating in Yaw About the Fin Midchord

Investigation of Minimum Drag and Maximum Lift-Drag Ratios of Several Wing-Body Combinations Including a Cambered Triangular Wing at Low Reynolds Numbers and at Supersonic Speeds

Investigation of Spoilers at a Mach Number of 1.93 to Determine the Effects of Height and Chordwise Location on the Section Aerodynamic Characteristics of a Two-Dimensional Wing

Investigation of Tantalum in a 3,800 Degrees Fahrenheit Supersonic Airstream

Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87

Investigation of the Longitudinal Aerodynamic Characteristics of a Trapezoidal-Wing Airplane Model With Various Vertical Positions of Wing and Horizontal Tail at Mach Numbers of 1.41 and 2.01

Analysis of Turbulent Flow and Heat Transfer in Noncircular Passages

Experimental Investigation of the Lateral Trim of a Wing-Propeller Combination at Angles of Attack Up to 90 Degrees With All Propellers Turning in the Same Direction

Theoretical Calculations of Supersonic Wave Drag at Zero Lift for a Particular Store Arrangement

Theoretical Rocket Performance of JP-4 Fuel with Several Fluorine-Oxygen Mixtures Assuming Equilibrium Composition

Theoretical Rocket Performance of Liquid Methane with Several Fluorine-Oxygen Mixtures Assuming Frozen Composition

Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight

Flight Tests of Two Smoke-Producing Devices Having Deacon Rocket Boosters

Heat Transfer for Mach Numbers Up to 2.2 and Pressure Distributions for Mach Numbers Up to 4.7 From Flight Investigations of a Flat-Face-Cone and a Hemisphere-Cone

Heat Transfer Measured on a Flat-Face Cylinder-Flare Configuration in Free Flight at Mach Numbers From 1.6 to 2.7

Further Investigation of Fatigue-Crack Propagation in Aluminum-Alloy Box Beams

Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model on the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 X 10(Exp 6) : Coord. No. AF-AM-70

Investigation of a Tilting-Wing Vertical-Take-Off-and-Landing Jet Airplane Model in Hovering and Transition Flight

Investigation of a High-Flow Transonic-Compressor Inlet Stage Having a Hub-Tip Radius of 0.35

Fatigue Behavior of Aircraft Structural Beams

Relationship of Metal Surfaces to Heat-Aging Properties of Adhesive Bonds

A Low-Speed Experimental Investigation of the Effect of a Sandpaper Type of Roughness on Boundary-Layer Transition

Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil

Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Longitudinal and lateral aerodynamic characteristics at combined angles of attack and sideslip of a generalized missile model having a rectangular wing at a Mach number of 4.08

Preliminary Analysis of a Nuclear-Powered Supersonic Airplane Using Ramjet Engines

Off-Design Performance of Divergent Ejectors

Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3

Preliminary Study of Airplane Configurations Having Tail Surfaces Outboard of the Wing Tips

Experimental Thermal Conductivities of the N2D4 Is in Equilibrium to 2NO2 System

An Exploratory Investigation at Mach Numbers of 2.50 and 2.87 of a Canard Bomber-Type Configuration Designed for Supersonic Cruise Flight

Feasibility of Nose-Cone Cooling by the Upstream Ejection of Solid Coolants at the Stagnation Point

Experimental Investigation of a 7-Inch-Tip-Diameter Transonic Turbine

Experimental Investigation of Turbojet-Engine Multiple-Loop Controls for Non-Afterburning and Afterburning Modes of Engine Operation

An Experimental Investigation of Two Internal-Compression Air-Inlet Designs Which Use Fluid Boundaries as a Means of Supersonic Compression

Temperature and Thermal-Stress Distributions in Some Structural Elements Heated at a Constant Rate

Section Thrust Coefficients for a Full-Scale, Three-Blade, Supersonic-Type Propeller Operating at Low and Negative Blade Angles

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