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- Longitudinal Frequency-Response Characteristics of the Douglas D-558-I Airplane as Determined From Experimental Transient-Response Histories to Mach Number of 0.90
- Longitudinal Frequency-Response and Stability Characteristics of the Douglas D-558-II Airplane as Determined From Transient Response to a Mach Number of 0.96
- The Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing Missile Having Half-Delta Tip Controls as Obtained From a Free-Flight Investigation at Transonic and Supersonic Speeds
- Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers From 1.1 to 1.93 as Determined From Free-Flight and Wind-Tunnel Investigation
- Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.70 to 1.37 of Rocket-Propelled Models Having a Modified Triangular Wing
- Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.75 to 1.5 of an Airplane Configuration Having a 60 Degree Swept Wing of Aspect Ratio 2.24 as Obtained From Rocket-Propelled Models
- A Low-Speed Experimental Study of the Directional Characteristics of a Sharp-Nosed Fuselage Through a Large Angle-of-Attack Range at Zero Angle of Sideslip
- Low-Speed Wind-Tunnel Investigation of the Effects of Propeller Operation at High Thrust on the Longitudinal Stability and Trim of a Twin-Engine Airplane Configuration
- Investigation of the Effects of Variations in the Reynolds Number Between 0.4 X 10(Exp 6) 3.0 X 10(Exp 6) on the Low-Speed Aerodynamic Characteristics of Three Low-Aspect-Ratio Symmetrical Wings With Rectangular Plan Forms
- An Investigation of Propeller Vibrations Excited by Wing Wakes
- Investigation of the Distribution of Lift, Drag, and Pitching Moment Between the Wing and Fuselage of a 1/30-Scale Semispan Model of the Bell X-5 Airplane at a Mach Number of 1.24 by the NACA Wing-Flow Method
- Investigation of Turbines for Driving Supersonic Compressors: 1: Design and Performance of First Configuration
- Investigation of Titanium Carbide Base Ceramals Containing Either Nickel or Cobalt for Use as Gas-Turbine Blades
- An Investigation of the Low-Speed Longitudinal Stability Characteristics of a Swept-Wing Airplane Model With Two Modifications to the Wing-Root Plan Form
- Investigation of the Low-Speed Aerodynamic Characteristics of a Variable-Sweep Airplane Model With a Twisted and Cambered Wing
- Stresses in a Two-Bay Noncircular Cylinder Under Transverse Loads
- Analysis of Fully Developed Turbulent Heat Transfer at Low Peclet Numbers in Smooth Tubes With Application to Liquid Metals
- Gust-Tunnel Investigation of a Delta-Wing Model With the Leading Edge Swept Back 60 Degrees
- Flow Separation From Rods Ahead of Blunt Noses at Mach Number 2.72
- Free-Flight Investigation of the Zero-Lift Drag of Several Wings at Supersonic Mach Numbers Extending to 2.6
- Flight Measurements of the Lateral Stability and Control Characteristics of a High-Speed Fighter Airplane
- Flight Test of a Radial-Burning Solid-Fuel Ram Jet
- Flight Measurements of the Effects of Surface Condition on the Supersonic Drag of Fin-Stabilized Parabolic Bodies of Revolution
- Force Tests of Three Thin Wings of Moderately Low Aspect Ratio at High Subsonic Mach Numbers
- Force and Pressure Investigation at Large Scale of a 49 Degree Sweptback Semispan Wing Having NACA 65A006 Sections and Equipped With Various Slat Arrangements
- Investigation at Transonic Speeds of the Effect of a Positive-Lift Balancing Tab on the Hinge-Moment and Lift-Characteristics of a Full-Span Flap on a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3
- An Investigation of a 0.16-Scale Model of the Douglas X-3 Airplane to Determine Means of Improving the Low-Speed Longitudinal Stability and Control Characteristics
- An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degrees Sweepback: Estimated Downwash Angles Derived From Pressure Measurements on the Tail at Mach Numbers of 1.40 and 1.59
- Investigation at Mach Number 2.93 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control
- Investigation at a Mach Number of 1.2 of Two 45 Degree Sweptback Wings Utilizing NACA 2-006 and NACA 65A006 Airfoil Sections
- An Investigation at Transonic Speeds of the Aerodynamic Characteristics of an Air Inlet Installed in the Root of a 45 Degree Sweptback Wing
- Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 2: Preliminary Analysis of Overall Performance
- Preliminary Survey of Boundary-Layer Development at a Nominal Mach Number of 5.5
- Calibration of AWS instrument shelter in Langley 300 MPH 7- by 10-foot tunnel
- Development of Metal-Bonding Adhesive FPL-710 With Improved Heat-Resistant Properties
- Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig
- The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow
- Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel
- The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section
- Aerodynamic Characteristics of a Refined Deep-Step Planing-Tail Flying-Boat Hull with Various Forebody and Afterbody Shapes
- Analogue-computer simulation of an autopilot servo system having nonlinear response characteristics
- Achievement of Continuous Wall Curvature in Design of Two-Dimensional Symmetrical Supersonic Nozzles
- The Aerodynamic Design of Supersonic Propellers from Structural Considerations
- Aerodynamic Characteristics of Three Deep-Step Planing-Tail Flying-Boat Hulls and a Transverse-Step Hull with Extended Afterbody
- Accuracy of Approximate Methods for Predicting Pressures on Pointed Nonlifting Bodies of Revolution in Supersonic Flow
- Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range
- Minimum Ignition of Six Pure Hydrocarbon Fuels of the C₂ and C₆ Series
- Behavior of materials under conditions of thermal stress
- NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results
- A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed