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- Effects of the Lateral Oscillation of Fixing the Rudder and Reflexing the Flaps on the Bell X-1 Airplane
- Exploratory Investigation of the Effect of Skewed Plain Nose Flaps on the Low-Speed Characteristics of a Large-Scale Triangular-Wing-Fuselage Model
- Low-Speed Static Stability Characteristics of a Canard Model with a 45 Degree Sweptback Wing and a 60 Degree Triangular Horizontal Control Surface
- Effect of an End Plate on the Aerodynamic Characteristics of a 20.55 Degree Sweptback Wing with an Aspect Ratio of 2.67 and a Taper Ratio of 0.5.: Transonic-Bump Method
- Determination of Minimum Moments of Inertia of Arbitrarily Shaped Areas, Such as Hollow Turbine Blades
- Lateral-Control Investigation at a Reynolds Number of 5,300,000 of a Wing of Aspect Ratio 5.8 Sweptforward 32 Degrees at the Leading Edge
- High-Speed Aerodynamic Characteristics of a Lateral-Control Model 2: Modified NACA 0012-64 Section with a 26.6-Percent-Chord, Plain, Trailing-Edge Aileron; Wing Unswept and Swept Back 45 Degrees
- Calculated Performance of Nuclear Turbojet Powered Airplane at Flight Mach Number of 0.9
- A Design Study of Leading-Edge Inlets for Unswept Wings
- Pressure Coefficients at Mach Numbers from 0.60 to 0.85 for a Semispan Wing with NACA 0012-64 Section, 20-Percent-Chord Plain Aileron, and 0 Degree and 45 Degree Sweepback
- Effect of Retractable Ignition Plug on Plug Fouling by Carbon Deposits
- Investigation at a Mach Number of 1.93 to Determine Lift, Drag, Pitching-Moment, and Average Downwash Characteristics for Several Missile Configurations Having Rectangular Wings and Tails of Various Spans
- Further Investigation of a Gas Turbine with National Bureau of Standards Body 4811C Ceramic Rotor Blades
- Altitude-Chamber Performance of British Roll-Royce Nene II Engine 4: Effect of Operational Variables on Temperature Distribution at Combustion-Chamber Outlets
- A Lift-Cancellation Technique in Linearized Supersonic-Wing Theory
- On the Theory of the Propagation of Detonation in Gaseous Systems
- On the Particular Integrals of the Prandtl-Busemann Iteration Equations for the Flow of a Compressible Fluid
- Laws of Flow in Rough Pipes
- Experiments to Determine Neighborhood Reactions to Light Airplanes With and Without External Noise Reduction
- Isentropic Phase Changes in Dissociating Gases and the Method of Sound Dispersion for the Investigation of Homogeneous Gas Reactions With Very High Speed
- Isentropic Phase Changes in Dissociating Gases and the Method of Sound Dispersion for the Investigation of Homogeneous Gas Reactions With Very High Speed
- Dependence of the Elastic Strain Coefficient of Copper on the Pre-Treatment
- The Development of a Hollow Blade for Exhaust Gas Turbines
- General Solution of Prandtl's Boundary-Layer Equation
- Formulas for the Supersonic Loading, Lift, and Drag of Flat Swept-Back Wings With Leading Edges Behind the Mach Line
- Effect of Intense Sound Waves on a Stationary Gas Flame
- Theory of Plane, Symmetrical Intake Diffusers
- Turbulence and Heat Stratification
- The Solution of the Laminar-Boundary-Layer Equation for the Flat Plate for Velocity and Temperature Fields for Variable Physical Properties and for the Diffusion Field at High Concentration
- The Stability of the Compression Cover of Box Beams Stiffened by Posts
- Contribution to the Problem of Buckling of Orthotropic Plates, With Special Reference to Plywood
- Some Effects of Nonlinear Variation in the Directional-Stability and Damping-in-Yawing Derivatives on the Lateral Stability of an Airplane
- Analysis of Turbulent Free-Convection Boundary Layer on Flat Plate
- The Diffusion of a Hot Air Jet in Air in Motion Part 2: The Flow Field in the Transition Zone
- Graphical Determination of Wall Temperatures for Heat Transfers Through Walls of Arbitrary Shape
- Investigation of Downwash, Sidewash, and Mach Number Distribution Behind a Rectangular Wing at a Mach Number of 2.41
- Some Features of Artificially Thickened Fully Developed Turbulent Boundary Layers with Zero Pressure Gradient
- Small Bending and Stretching of Sandwich-Type Shells
- Supersonic Flow Around Circular Cones at Angles of Attack
- A General Integral Form of the Boundary-Layer Equation for Incompressible Flow With an Application to the Calculation of the Separation Point of Turbulent Boundary Layers
- The External-Shock Drag of Supersonic Inlets Having Subsonic Entrance Flow
- Preliminary Investigation of Reflections of Oblique Waves from a Porous Wall
- Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine: 1: Rotor Blades With 10 Tubes in Cooling-Air Passages
- Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Tail Attached to a Segment of the Foreshortened Body
- Wind-Tunnel Investigation of a 1/6-Scale Model of the Bumblebee XPM Missile at High Subsonic Speeds
- Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 2: Rotor Blades With 15 Fins in Cooling-Air Passages
- Effect of Nose Shape and Wing Thickness Ratio on the Drag at Zero Lift of a Missile Having Triangular Wings and Tails
- Investigation of Power Requirements for Ice Prevention and Cyclical De-Icing of Inlet Guide Vanes with Internal Electric Heaters
- Model Ditching Investigations of Three Airplanes Equipped With Hydro-Skis
- Photomicrographic Investigation of Spontaneous Freezing Temperatures of Supercooled Water Droplets