Browse TRAIL Inventories

Theory and apparatus for measurement of emissivity for radiative cooling of hypersonic aircraft with data for Inconel and Inconel X

Low-speed pressure-distribution investigation of a thin-delta-wing-fuselage model having double slotted flaps and spoilers

The linearized subsonic flow about symmetrical nonlifting wing-body combinations

Methods for obtaining desired helicopter stability characteristics and procedures for stability predictions

A method utilizing data on the spiral, roll-subsidence, and dutch roll modes for determining lateral stability derivatives from flight measurements

Momentum transfer for flow over a flat plate with blowing

On the minimization of airplane responses to random gusts

Determination of surge and stall limits of an axial-flow turbojet engine for control applications

Experimental investigation of the simulation of atmospheric entry of ballistic missiles

Performance at High Temperatures and Pressures of an Annular Turbojet Combustor Having Articulated Liner Walls

Performance of a Supersonic Ramp-type Side Inlet With Ram-scoop Throat Bleed and Varying Fuselage Boundary-layer Removal Mach Number Range 1.5 to 2.0

Performance of Twin-Duct Variable-Geometry Side Inlets at Mach Numbers of 1.5 to 2.0

Preliminary Evaluation of the Wing Leading Edge as a Missile-Mounting Location

Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Canard Missile During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination at Zero Sideslip

A Flight and Analog Study of the Effect of Elevating the Radar-Boresight Axis Upon Stability and Tracking Performance of an Automatically Controlled Interceptor

Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration With a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers From 1.2 to 2.1

Factors Affecting Loads at Hypersonic Speeds

Experimental Investigation of Diffuser Pressure Ratio Control With Shock Positioning Limit on 28 Inch Ram-Jet Engine

A Review of NACA Research Through 1954 on Boron Compounds as Fuels for Jet Aircraft (Project Zip)

Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives

Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System

Transonic Flight Evaluation of the Effects of Fuselage Extension and Indentation on the Drag of a 60-Degree Delta Wing Interceptor Airplane

Transonic Flutter Characteristics of a Cambered A-Plan-Form Wing With and Without Simulated Nacelles

Results of the Flight Test of a 0.13-Scale Rocket-Boosted Model of the McDonnell F4H-1 Airplane Between Mach Numbers of 0.20 and 1.90

Transonic Wind-Tunnel Investigation of Static-Pressure Fluctuations in Duct of a Scale Inlet Model of a Supersonic Fighter-Bomber Airplane

Wind-Tunnel Flutter Tests at Mach Numbers up to 3.0 of Boeing Wing Models for Weapons System 110A

Wind-Tunnel Investigation of the Effect of Spin on the Aerodynamic Characteristics of a 60-Millimeter T-24 Mortar Shell With Several Tail-Fin Configurations

Flight Investigation of a Liquid Hydrogen Fuel System

Altitude Starting Tests of a Small Solid Propellant Rocket

Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets

Additional Experiments With Flat-Top Wing- Body Combinations at High Supersonic Speeds

Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination

Wind-Tunnel Investigation of Mutual Interference Loads on a Supersonic Bomber Configuration and Store During Separation at Mach Numbers of 1.57, 1.77, and 2.01

Wind-Tunnel Measurement of Static Forces on Internally Carried Bombs of Two Different Bluff Shapes in the Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.6

Impingement of Cloud Droplets on 36.5-Percent-Thick Joukowski Airfoil at Zero Angle of Attack and Discussion of Use as Cloud Measuring Instrument in Dye-Tracer Technique

Local Heat Transfer to Blunt Noses at High Supersonic Speeds

Measurement of Static Forces on Externally Carried Bombs of Fineness Ratios 7.1 and 10.5 in the Flow Field of a Swept-Wing Fighter- Bomber Configuration at a Mach Number of 1.6

Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01

Evaluation of Hydrogen Fuel in a Full-Scale Afterburner

Influence of Automatic Control of Roll Coupling and Pitch-Up on Tail Loads

Influence of Boric Oxide Deposition on Turbojet-Engine Operation

A Note on the Ability to Predict Transonic Drag-Rise Changes Due to Model Modifications

NACA Conference on Aircraft Loads, Structures, and Flutter

Comparative Study of Turbofan and Turbojet Engines

Comparison and Evaluation of Two Model Techniques Used in Predicting Bomb-Release Motions

Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine

The Design and Cascade Tests of Free-Streamline and Full-Contour 160 Degree Turning Supersonic-Turbine-Blade Sections

Calculation of External-Store Loads and Correlation With Experiment

Comparison of Experimental and Theoretical Zero-Lift Wave-Drag Results for Various Wing-Body-Tail Combinations at Mach Numbers Up to 1.9

Aerodynamic Loads on Tails at High Angles of Attack and Sideslip


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