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Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06

Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Several Mach Numbers and Simulated Altitudes

Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine

Heat Transfer in Regions of Separated and Reattached Flows

In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System

Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0

Investigation of Static Pressures and Boundary-Layer Characteristics on the Forward Parts of Nine Fuselages of Various Cross-Sectional Shapes at M Infinity Equal 2.01

Analysis of Fluorine Addition to the Vanguard First Stage

Brief Studies of Turbojet Combustor and Fuel-System Operation With Hydrogen Fuel at -400 Degrees F

Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61

Simplified Theory for Dynamic Relation of Ramjet Pressures and Fuel Flow

Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations

Thermal Stability of a Commercial Propyl Pentaborane (HEF-2) in the Range 147 Degree to 190 Degree C

A Summary of the Longitudinal and Lateral Stability and Control Characteristics Obtained From Rocket-Model Tests of a Swept-Wing Fighter-Type Airplane at Mach Numbers From 0.5 to 1.9

Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2

Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01

Total-Pressure Distortion and Recovery of Supersonic Nose Inlet With Conical Centerbody in Subsonic Icing Conditions

Preliminary Investigation of Dynamic Lateral Stability Characteristics of a Configuration of the North American X-15 Research Airplane

Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane

Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power

Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration

Flutter Experiments With Various Control Configurations

Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control

Effects of Free-Stream Reynolds Number, Engine Installation, and Model Scale on Stability Characteristics of a Translating-Spike Inlet at Mach 2.0

Heat-Exchanger-Core Weights for Use With Hydrogen-Expansion Turbine

Hydrogen for Turbojet and Ramjet Powered Flight

Experimental Evaluation of Swirl Can Elements for Hydrogen Fuel Combustor

Performance and Operational Characteristics of Pentaborane Fuel in 48-Inch-Diameter Ram-Jet Engine

Wind-Tunnel Investigation of a Wing-Root Inlet Configuration With Various Modifications at Mach Numbers of 1.41, 1.81, and 2.01

Origin and Prevention of Crash Fires in Turbojet Aircraft

Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine

Steady Nuclear Combustion in Rockets

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

The Principles of Turbulent Heat Transfer

Wind-Tunnel Investigation of the Republic F-105 Inlet with Various Modifications at Mach Numbers 1.41, 1.81, and 2.01

On the Use of the Harmonic Linearization Method in the Automatic Control Theory

Annual Report of the National Advisory Committee for Aeronautics (41st). Administrative Report Including Technical Report Nos. 1210 to 1253

NACA Zero Power Reactor Facility Hazards Summary

Preliminary Note on a Correlation of a Boundary-Layer Transition Results on Highly Cooled Blunt Bodies

Heat of Combustion of the Product Formed by the Reaction of Acetylene, Ethylene, and Diborane

Effect of Some External Crosswise Stiffeners on the Heat Transfer and Pressure Distribution on a Flat Plate at Mach Numbers of 0.77, 1.39, and 1.98

Concluding Report of Free-Spinning, Tumbling, and Recovery Characteristics of a 1/18-Scale Model of the Ryan X-13 Airplane, Coord. No. AF-199

Aerodynamic Forces on a Vibrating Unstaggered Cascade

Measurements of Heat Transfer and Boundary-Layer Transition on an 8-Inch-Diameter Hemisphere-Cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88

On the Spectrum of Natural Oscillations of Two-Dimensional Laminar Flows

Reflection and Refraction of Acoustic Waves by a Shock Wave

The Effect of Solid Admixtures on the Velocity of Motion of a Free Dusty Air Jet

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