Browse TRAIL Inventories

Statistical Study of Turbulence: Spectral Functions and Correlation Coefficients

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

Slip-Flow Heat Transfer From Cylinders in Subsonic Airstreams

Some Effects of Fin Leading-Edge Shape on Aerodynamic Heating at Mach Number 2.0 at a Stagnation Temperature of About 2,600 Degrees R

Some Effects of Reynolds Number on the Stability of a Series of Flared-Body and Blunted-Cone Models at Mach Numbers Form 1.62 to 6.86

Some Effects of Mass Ratio on the Transonic Flutter Characteristics of Untapered 45 Degree Sweptback Wings of Aspect Ratios 2 and 3.5

Some Measurements of Aerodynamic Forces and Moments at Subsonic Speeds on a Rectangular Wing of Aspect Ratio 2 Oscillating About the Midchord

Rocket-Model Investigation to Determine the Lift and Pitching Effectiveness of Small Pulse Rockets Exhausted From the Fuselage Over the Surface of an Adjacent Wing at Mach Numbers From 0.9 to 1.8

Shape of Initial Portion of Boundary of Supersonic Axisymmetric Free Jets at Large Jet Pressure Ratios

Preliminary Survey of Propulsion Using Chemical Energy Stored in the Upper Atmosphere

Theoretical Investigation of Subsonic Oscillatory Blade-Row Aerodynamics

Behavior of Some Materials and Shapes in Supersonic Free Jets at Stagnation Temperatures Up to 4,210 Degrees F, and Descriptions of the Jets

Effects of Propeller Position and Overlap on the Slipstream Deflection Characteristics of a Wing-Propeller Configuration Equipped With a Sliding and Fowler Flap

Transient Temperature Distribution in a Two-Component Semi-Infinite Composite Slab of Arbitrary Materials Subjected to Aerodynamic Heating With a Discontinuous Change in Equilibrium Temperature or Heat-Transfer Coefficient

Transonic Characteristics of Outboard Ailerons on a 4-Percent-Thick 30 Degree Sweptback Wing, Including Some Effects of Aileron Trailing-Edge Thickness and Aerodynamic Balance

Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane

Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane

Qualitative Measurements of the Effective Heats of Ablation of Several Materials in Supersonic Air Jets at Stagnation Temperatures Up to 11,000 Degrees F

Subsonic Flight Investigation of Methods to Improve the Damping of Lateral Oscillations by Means of a Viscous Damper in the Rudder System in Conjunction With Adjusted Hinge-Moment Parameters

Summary of Flutter Experiences as a Guide to the Preliminary Design of Lifting Surfaces on Missiles

Some Effects of Roughness on Stagnation-Point Heat Transfer at a Mach Number of 2, a Stagnation Temperature of 3,530 F, and a Reynolds Number of 2.5 X 10(Exp 6) Per Foot

Use of Shock-Trap Bleed to Improve Pressure Recovery of Fixed-and Variable-Capture-Area Internal-Contraction Inlets; Mach Number 2.0 to 3.0

Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude

Viscous Flows in Inlets

Wind-Tunnel Investigation at Mach Numbers From 0.6 to 1.4 of Several Ejected Pilot-Seat Models

Wind-Tunnel Investigation of the Effect of Sweep and Taper Ratio on Effectiveness of Spoiler-Slot-Deflector Controls on Aspect-Ratio-4 Wings at Transonic Speeds

Wind-Tunnel Investigation of the Effects of Lip Geometry on Drag and Pressure Recovery of a Normal-Shock Nose Inlet on a Body of Revolution at Mach Numbers of 1.41 and 1.81

Wind-Tunnel Investigation of the Low-Speed Stability and Performance Characteristics of a Jet-Powered Low-Aspect-Ratio Vertical-Take-Off-and-Landing Configuration With Engines Buried in Tiltable Wings

Transonic Investigation of an Axial-Flow Compressor Rotor With a Contracted Exit Annulus

Transonic Lateral and Longitudinal Aerodynamic Characteristics of a Lateral-Control System Employing Rotatable Airfoils Mounted Vertically at the Wing Tips of an Unswept Wing-Fuselage-Tail Combination

Effect of Forging Temperature and Heat Treatment on the Performance of Inconel 700 Buckets at 1625 Degrees F in a J33-9 Turbojet Engine

Evaluation of Three Injectors in a 2400-Pound-Thrust Rocket Engine Using Liquid Oxygen and Liquid Ammonia

An Analysis of the Optimization of a Beam Rider Missile System

Wind-Tunnel Data on the Longitudinal and Lateral-Directional Rotary Derivatives of a Straight-Wing, Research Airplane Configuration at Mach Numbers From 2.5 to 3.5

A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds

Wind-Tunnel Investigation of the Use of Leading-Edge and Trailing-Edge Area-Suction Flaps on a 13-Percent-Thick Straight Wing and Fuselage Model

Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Four Aluminum-Alloy Models of 20-Inch Chord and Span With 0.064-Inch-Thick Skin, 0.025-Inch-Thick Ribs and Webs, and Zero, One, Two, or Three Chordwise Ribs

Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: An Aluminum-Alloy Model of 40-Inch Chord With 0.125-Inch-Thick Skin


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