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- A Semiempirical Correlation of Afterburner Combustion Efficiency and Lean-Blowout Fuel-Air-Ratio Data with Several Afterburner-Inlet Variables and Afterburner Lengths
- Flight-Test Investigation on the Langley Control-Line Facility of a Model of a Propeller-Driven Tail-Sitter-Type Vertical-Take-Off Airplane with Delta Wing During Rapid Transitions
- Effect of Transient Heating on Vibration Frequencies of Some Simple Wing Structures
- Effects of Jet Exhausts on Flight-Determined Longitudinal and Lateral Dynamic Stability Characteristics of the Douglas D-558-II Research Airplane
- Dynamic Longitudinal Stability Characteristics of a Swept-Wing Fighter-Type Airplane at Mach Numbers Between 0.36 and 1.45
- Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 4: Performance of Tapered-Tip Rotor Configuration with Reset Blade Angles
- Instrument Flight Trials with Helicopter Stabilized in Attitude About Each Axis Individually
- Three-Degree-of Freedom Evaluation of the Longitudinal Transfer Functions of a Supersonic Canard Missile Configuration Including Changes in Forward Speed
- Analysis of Limitations Imposed on One-Spool Ducted-Fan-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0, 0.6, and 0.8
- Experimental Investigation of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages 4: Blade-Element Performance
- High-Altitude Performance of J71-A-11 Turbojet Engine and Its Components Using JP-4 and Gaseous-Hydrogen Fuels
- Preliminary Investigation of the Effect of Surface Treatment on the Strength of a Titanium Carbide - 30 Percent Nickel Base Cermet
- Some Aspects of Fail-Safe Design of Pressurized Fuselages
- Bursting Strength of Unstiffened Pressure Cylinders with Slits
- Hinge-Moment and Effectiveness Characteristics of an Aspect-Ratio-8.2 Flap-Type Control on a 60 Degree Delta Wing at Mach Numbers from 0.72 to 1.96
- Experimental Investigation of Modified Cast-Cored Blades Having Hollow Tip Sections
- Effect of Fluid-System Parameters on Starting Flow
- Measurements of Runway Roughness of Four Commercial Airports
- Analysis of Static Aeroelastic Behavior of Low-Aspect-Ratio Rectangular Wings
- 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