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- The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 3 - Swept-Wing Fighter-Bomber Configuration With Large and Small Stores. Mach Number, 1.61
- The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations 2 - Swept-wing Heavy-bomber Configuration With Large Store Nacelle. Lateral Forces and Pitching Moments, Mach Number, 1.61
- The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 4. - Delta-Wing Heavy-Bomber Configuration With Large Store. Mach Number, 1.61
- Analysis of Limitations Imposed on One-Spool Turbojet-Engine Designs by Turbines Having Downstream Stators at 0, 2.0, and 2.8 Flight Mach Numbers
- Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Mach Numbers of 1.41, 1.61, and 2.01
- An Investigation of Jet Effects on Adjacent Surfaces
- Flight Investigation of a Roll-Stabilized Ramjet Test Vehicle Over a Mach Number Range of 2.3 to 2.7
- Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration With a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.8
- Low-Temperature Chemical Starting of a 200-Pound-Thrust JP-4 - Nitric Acid Rocket Engine Using a Three-Fluid Propellant Valve
- An Investigation of the Longitudinal Stability Characteristics of Three Specialized Store Configurations at Transonic Speeds
- Investigation of Porous Gas-Heated Leading-Edge Section for Icing Protection of a Delta Wing
- NACA Conference on Aerodynamics of High Speed Aircraft
- Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail
- Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds
- Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight
- Investigation of a 1/4-Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Lateral Control and Directional Stability and Control Characteristics of Model Equipped With Drooped, Supersonic-Type, Elliptical Wing-Root Inlet
- Investigation of a 1/4 Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Longitudinal Stability and Control and Horizontal-Tail Hinge-Moment and Normal-Force Characteristics of the Model Equipped With a Drooped Supersonic-Type Elliptical Wing-Root Inlet
- A Comparison of the Maneuvering Performance of a Monowing Versus a Cruciform Missile
- Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25
- Analysis of Low-Temperature Nuclear-Powered Ramjet Missile for High Altitudes
- Chemical and Physical Properties of Modified Hi-Cal-2
- Analysis of stresses in the plastic range around a circular hole in a plate subjected to uniaxial tension
- Preliminary Investigation of a Submerged Air Scoop Utilizing Boundary-Layer Suction to Obtain Increased Pressure Recovery
- A Preliminary Investigation of Aerodynamic Characteristics of Small Inclined Air Outlets at Transonic Mach Numbers
- Preliminary Investigation of Properties of High-Temperature Brazed Joints Processed in Vacuum or in Molten Salt
- An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98
- Two Miniature Temperature Recorders for Flight Use
- Study of Screeching Combustion in a 6-Inch Simulated Afterburner
- The Zero-Lift Wave Drag of a Particular Family of Unswept, Tapered Wings With Linearly Varying Thickness Ratio
- Analysis of the Horizontal-Tail Loads Measured in Flight on a Multiengine Jet Bomber
- Prediction of Downwash Behind Swept-Wing Airplanes at Subsonic Speed
- Effective Moment of Inertia of Fluid in Offset, Inclined, and Swept-Wing Tanks Undergoing Pitching Oscillations
- Effect of Ammonia Addition on Limits of Flame Propagation for Isooctane-Air Mixtures at Reduced Pressures and Elevated Temperatures
- Analysis of Laminar Forced-Convection Heat Transfer in Entrance Region of Flat Rectangular Ducts
- Description and Analysis of a Rocket-Vehicle Experiment on Flutter Involving Wing Deformation and Body Motions
- Design and Performance of Throttle-Type Fuel Controls for Engine Dynamic Studies
- Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration With a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.
- An Investigation of the Discharge and Drag Characteristics of Auxiliary-Air Outlets Discharging Into a Transonic Stream
- Experimental Investigation of Eccentricity Ratio, Friction, and Oil Flow of Long and Short Journal Bearings With Load-Number Charts
- Analysis of Fully Developed Turbulent Heat Transfer and Flow in an Annulus With Various Eccentricities
- Icing Limit and Wet-Surface Temperature Variation for Two Airfoil Shapes Under Simulated High-Speed Flight Conditions
- Friction Study of Aircraft Tire Material on Concrete
- Over-All Performance of J65-B3 Turbojet Engine for Reynolds Number Indices from 0.8 to 0.2
- Reduction of the Shimmy Tendency of Tail and Nose-Wheel Landing Gears by Installation of Specially Designed Tires
- Spatial Burnout in Water Reactors with Nonuniform Startup Distributions of Uranium and Boron
- A Theoretical and Experimental Investigation of the Lift and Drag Characteristics of Hydrofoils at Subcritical and Supercritical Speeds
- Lift on a Bent, Flat Plate
- Wind-Tunnel Investigation at Low Speed of the Yawing, Pitching, and Static Stability Characteristics of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109
- Full-Scale-Wind-Tunnel Tests of a 35 Degree Sweptback Wing Airplane With High-Velocity Blowing Over the Training-Edge Flaps
- From Linear Mechanics to Nonlinear Mechanics