TRAIL - Technical Report Archive and Image Library

Wind-Tunnel Investigation at Low Speed of the Static Longitudinal and Lateral Stability Characteristics of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane

Analytical Derivation and Experimental Evaluation of Short-Bearing Approximation for Full Journal Bearing

Flight Tests of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane in a Setup Simulating that Proposed for Captive-Flight Tests in a Hangar, TED No. NACA DE 368

Estimation of the Maximum Angle of Sideslip for Determination of Vertical-Tail Loads in Rolling Maneuvers

Elastic Buckling Under Combined Stresses of Flat Plates With Integral Waffle-Like Stiffening

Air Admixture to Exhaust Jets

Investigation of the Spinning and Tumbling Characteristics of a 1/25-Scale Model of the Lockheed XFV-1 Airplane in the Langley 20-Foot Free-Spinning Tunnel

Low-Speed Investigation of the Static Lateral Stability and Control Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating

Flight Test Results of Rocket-Propelled Buffet-Research Models Having 45 Degree Sweptback Wings and 45 Degree Sweptback Tails Located in the Wing Chord Plane

Altitude Performance and Operational Characteristics of YJ71-A-7 Turbojet Engine

Low-Speed Longitudinal Stability Characteristics of a 1/6-Scale Model of the Republic XF-84H Airplane with the Propeller Operating

Method of Estimating the Incompressible-Flow Pressure Distribution of Compressor Blade Sections at Design Angle of Attack

Flight Investigation of the Stability and Control Characteristics of a 0.13-Scale Model of the Convair XFY-1 Vertically Rising Airplane During Constant-Altitude Transitions, TED No. NACA DE 368

Flight Investigation of Nine Reduced-Scale (1:3.75) Hermes A-2S Rocket-Motor Test Vehicles

Investigation of the Attenuation of Plane Shock Waves Moving Over Very Rough Surfaces

Theoretical Study of the Tunnel-Boundary Lift Interference Due to Slotted Walls in the Presence of the Trailing-Vortex System of a Lifting Model

Heat of Combustion of the Product Formed by the Reaction of Diborane with 1,3-Butadiene

Analysis of Landing-Gear Behavior

Investigation of the Effects of Propeller Operation on the Low-Speed Stability and Control Characteristics of a 1/6-Scale Model of a Revised Configuration of the Republic XF-84H Airplane

Aerodynamic Characteristics in Pitch and Sideslip at High Subsonic Speeds of a 1/14-Scale Model of the Grumman XF104 Airplane with Wing Sweepback of 42.5 Degrees

Drag Measurements on Equivalent Bodies of Revolution of Six Configurations of the Convair MX-1964 (Originally MX-1626) Proposed Supersonic Bomber

High-Speed Wind-Tunnel Tests of a 1/16-Scale Model of the D-558 Research Airplane Lift and Drag Characteristics of the D-558-1 and Various Wing and Tail Configurations

Combustion in the Wake as a Means of Body-Drag Reduction as Determined from Free-Flight Tests of 40-Millimeter Shells

Preflight Tests and Flight Performance of a 6.5-Inch Diameter Ram-Jet Engine

Performance of Double-Shroud Ejector Configuration With Primary Pressure Ratios From 1.0 to 10

A Preliminary Investigation of the Power Requirements of Slotted Test Sections

Preliminary Results of Stability and Control Investigation of the Bell X-5 Research Airplane

A Preliminary Study by Means of Electrical Frequency-Analysis Techniques of the Response of an Airplane Structure During Buffeting

Experimental Investigation of the Flow Field Behind an Aspect-Ratio-10 Hydrofoil Near the Water Surface

Flight Investigation at Mach Numbers From 0.67 to 1.81 of the Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing Missile Configuration Having an All-Movable Tail

Exploratory Investigation of Transpiration Cooling to Alleviate Aerodynamic Heating on an 8 Degree Cone in a Free Jet at a Mach Number of 2.05

Flight-Determined Pressure Distributions Over the Wing of the Bell X-1 Research Airplane (10-Percent-Thick Wing) at Subsonic and Transonic Speeds

Flight Determination of the Pressure Recovery and Drag Characteristics of a Twin Side-Inlet Model at Transonic Speeds

Flight Determination of Drag of Normal-Shock Nose Inlets With Various Cowling Profiles at Mach Numbers From 0.9 to 1.5

An Experimental Investigation of Wheel Spin-Up Drag Loads

An Experimental Investigation of the Zero-Lift-Drag Characteristics of Symmetrical Blunt-Trailing-Edge Airfoils at Mach Numbers From 2.7 to 5.0

Flight Determination of the Longitudinal Stability in Accelerated Maneuvers at Transonic Speeds for the Douglas D-558-II Research Airplane Including the Effects of an Outboard Wing Fence

Some Effects of Leading-Edge Roughness on the Aileron Effectiveness and Drag of a Thin Rectangular Wing Employing a Full-Span Plain Aileron at Mach Numbers From 0.6 to 1.5

Some Experimental Effects of Afterbody Shape on the Zero-Lift Drag of Bodies for Mach Numbers Between 0.8 and 1.3

Preliminary Theoretical Investigation of Several Methods for Stabilizing the Lateral Motion of a High-Speed Fighter Airplane Towed by a Single Cable

Preliminary Results From a Limited Investigation of the Use of Controls During Service Operational Training With Fighter Airplanes

Preliminary Experimental Investigation of the Flight of a Person Supported by a Jet Thrust Device Attached to His Feet

Preliminary Investigation in J33 Turbojet Engine of Several Root Designs for Ceramal Turbine Blades

A Preliminary Investigation at Mach Number 1.91 of an Inlet Configuration Designed for Insensitivity to Positive Angle-of-Attack Operation

Preliminary Investigation of Several Root Designs for Cermet Turbine Blades in Turbojet Engine 2: Root Design Alterations

Preliminary Measurements of Static Longitudinal Stability and Trim for the XF-92A Delta-Wing Research Airplane in Subsonic and Transonic Flight

A Preliminary Investigation at Mach Number 1.91 of a Diffuser Employing a Pivoted Cone to Improve Operation at Angle of Attack

Preliminary Investigation of the Total-Pressure-Recovery Characteristics of a Symmetric and Asymmetric Nose Inlet Over a Wide Range of Angle of Attack at Supersonic Mach Numbers

Preliminary Investigation of the Total-Pressure-Recovery Characteristics of a 15 Degree Semiangle Movable-Cone Variable-Geometry Ram-Jet Inlet at Free-Jet Mach Numbers of 1.62, 2.00, 2.53, and 3.05

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