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- An Approximate Solution for Axially Symmetric Flow Over a Cone With an Attached Shock Wave
- Some Measurements of Time and Space Correlation in Wind Tunnel
- The Theories of Turbulence
- Interaction of a Free Flame Front With a Turbulence Field
- Nonlifting Wing-Body Combinations With Certain Geometric Restraints Having Minimum Wave Drag at Low Supersonic Speeds
- On the Mechanism of Buckling of a Circular Cylindrical Shell Under Axial Compression
- Optimum Flight Paths of Turbojet Aircraft
- Steady Properly-Banked Turns of Turbojet-Propelled Airplanes
- A Method of Quadrature for Calculation of the Laminar and Turbulent Boundary Layer in Case of Plane and Rotationally Symmetrical Flow
- General Solutions of Optimum Problems in Nonstationary Flight
- Incompressible Flutter Characteristics of Representative Aircraft Wings
- Effect of Interaction on Landing-Gear Behavior and Dynamic Loads in a Flexible Airplane Structure
- Theory of Dynamic Creep
- Theory of Reversible and Nonreversible Cracks in Solids
- Influence of Alloying upon Grain-Boundary Creep
- Metallography of Aluminum and Its Alloys: Use of Electrolytic Polishing
- Influence of Hot-Working Conditions on High-Temperature Properties of a Heat-Resistant Alloy
- Linearized Lifting-Surface and Lifting-Line Evaluations of Sidewash Behind Rolling Triangular Wings at Supersonic Speeds
- Contributions on the Mechanics of Boundary-Layer Transition
- Charts for Estimating Performance of High-Performance Helicopters
- Characteristics of Turbulence in Boundary Layer with Zero Pressure Gradient
- Some Results of Flight Testing of Ski-Equipped Aircraft at the Naval Air Test Center
- Investigation of a Cermet Gas-Turbine-Blade Material of Titanium Carbide Infiltrated With Hastalloy C
- Study of Effects of Microstructure and Anisotropy on Fatigue of 23S-T4 Aluminum Alloy
- Application of Stream-Filament Techniques to Design of Diffuser Between Compressor and Combustor in a Gas-Turbine Engine
- Flight Measurements of the Dynamic Lateral and Longitudinal Stability of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback
- The Effect of a 4-Percent-High Spoiler on Buffeting Forces on a NACA 65(Sub 06)A004 Two-Dimensional Airfoil at Subsonic Mach Numbers
- Effects of Wing Position and Fuselage Size on the Low-Speed Static Rolling Stability Characteristics of a Delta-Wing Model
- Hydrodynamic Pressure Distribution Obtained With a Streamline Body Equipped With Chine Strips
- Free-Flight Tests to Determine the Power-on and Power-Off Pressure Distribution and Drag of the NACA RM-10 Research Vehicle at Large Reynolds Numbers Between Mach Numbers 0.8 and 3.0
- Theoretical Calculations of the Pressures, Forces, and Moments Due to Various Lateral Motions Acting on Thin Isolated Vertical Tails With Supersonic Leading and Trailing Edges
- Investigation of the Effects of an Airfoil Section Modification on the Aerodynamic Characteristics at Subsonic and Supersonic Speeds of a Thin Swept Wing of Aspect Ratio 3 in Combination With a Body
- Thermal Analysis of Sodium Hydroxide Containing the Reaction Products of Sodium Hydroxide and Chromium Metal
- Preliminary Investigation of Several Root Designs for Cermet Turbine Blades in Turbojet Engine 3: Curved-Root Design
- Meteorological Problems Associated With Commercial Turbojet-Aircraft Operation
- A Method for Determining the Composition of Methanol-Trimethyl Borate Mixtures
- Summary of the Flight Conditions and Maneuvers in Which Maximum Wing and Tail Loads Were Experienced on a Swept-Wing Fighter Airplane
- A Theoretical Analysis of a Simple Aerodynamic Device to Improve the Longitudinal Damping of a Cruciform Missile Configuration at Supersonic Speeds
- Effect of Taper Ratio on Lift, Drag, and Pitching-Moment Characteristics of Thin Wings of Aspect Ratio 3 With 53.1 Degrees Sweepback of Leading Edge at Subsonic and Supersonic Speeds
- A Simplified Method for Calculating Aeroelastic Effects on the Roll of Aircraft
- Behavior of the Bell X-1A Research Airplane During Exploratory Flights at Mach Numbers Near 2.0 and at Extreme Altitudes
- Comparison of the Static Stability of a 68.7 Degree Delta-Wing Model with Dihedral and a Twisted and Cambered Wing Model of the Same Plan Form
- Low-Speed Investigation of the Effects of Wing Tanks and Speed Brakes on the Static Stability of a Model Having a 40 Degree Swept Wing
- Effect of Dissolved Oxygen on the Filterability of Jet Fuels for Temperatures Between 300 Degrees and 400 Degrees Fahrenheit
- Note on Hovering Turns with Tandem Helicopters
- Effects of Wing-Mounted Tank-Type Stores on the Low Lift Buffeting and Drag of a Swept-Wing Airplane Configuration Between Mach Numbers of 0.8 and 1.3
- Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane
- Flight Determination of the Longitudinal Stability and Control Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback
- Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 2: Stage and Blade-Element Performance
- Investigation of Two Short Annular Diffuser Configurations Utilizing Section and Injection as a Means of Boundary-Layer Control