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- Theoretical Investigation of the Performance of Proportional Navigation Guidance Systems: Effect of Method of Positioning the Radar Antenna on the Speed of Response
- Theoretical Investigation of the Stability at Negative Static Margins of a Supersonic Missile With an Autopilot Sensitive to Pitch Angle and Pitching Velocity
- The Normal Component of the Induced Velocity in the Vicinity of a Lifting Rotor and Some Examples of Its Application
- Preliminary Investigation of a New Type of Supersonic Inlet
- The Ames Supersonic Free-Flight Wind Tunnel
- Supplementary Bibliography of NACA Reports Related to Instrumentation and Research Techniques
- Performance Characteristics of a Normal-Shock Side Inlet Located Downstream of a Canard Control Surface at Mach Numbers of 1.5 and 1.8
- A Method for Estimating Speed Response of Gas-Turbine Engines
- Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 12: Cooling Effectiveness of a Blade With an Insert and With Fins Made of a Continuous Corrugated Sheet
- An Investigation at Subsonic Speeds of the Rolling Effectiveness of a Small Perforated Spoiler on a Wing Having 45 Degrees of Sweepback
- Dynamic Response of Turbine-Blade Temperature to Exhaust-Gas Temperature for Gas-Turbine Engines
- Experimental Investigation of Axial-Flow Compressor Stator Blades Designed to Obtain High Turning Angles by Means of Boundary-Layer Suction
- Use of Fences to Increase Uniformity of Boundary Layer on Side Walls of Supersonic Wind Tunnels
- Radiant Heat Transfer From Flames in a Single Tubular Turbojet Combustor
- Some Dynamic Characteristics of a Turbojet Engine for Large Accelerations
- Spreading of Exhaust Jet From 16 Inch Ream Jet at Mach Number 2.0
- A Meter for Timing the Flow of Very Small Volumes of a Gas
- A Study of the Application of Power-Spectral Methods of Generalized Harmonic Analysis to Gust Loads on Airplanes
- Effect of Geometry on Secondary Flows in Blade Rows
- Chordwise and Compressibility Corrections to Slender-Wing Theory
- Lift, Drag, and Pitching Moment of Low-Aspect-Ratio Wings at Subsonic and Supersonic Speeds: Plane Triangular Wing of Aspect Ratio 3 With Air-to-Air Missile Models Mounted Externally
- Method of Estimating the Stick-Fixed Longitudinal Stability of Wing-Fuselage Configurations Having Unswept or Swept Wings
- Method and Graphs for the Evaluation of Air-Induction Systems
- A Study of Second-Order Supersonic Flow Theory
- An Investigation at Mach Numbers 2.98 and 2.18 of Axially Symmetric Free-Jet Diffusion with a Ram-Jet Engine
- Some Wind-Tunnel Results of an Investigation of the Flutter of Sweptback- and Triangular-Wing Models at Mach Number 1.3
- Use of Choked Nozzle Technique and Exhaust Jet Diffuser for Extending Operable Range of Jet-Engine Research Facilities
- A Study of the Use of Freon-12 as a Wind-Tunnel Testing Medium at Low Supersonic Mach Numbers
- Low-Speed Lateral-Control Investigation of a Flap-Type Spoiler Aileron With and Without a Deflector and Slot on a 6-Percent-Thick, Tapered, 45 Degree Sweptback Wing of Aspect Ratio 4
- An Application of the Rocket-Propelled-Model Technique to the Investigation of Low-Lift Buffeting and the Results of Preliminary Tests
- Effects of Some Primary Variables of Rectangular Vortex Generators on the Static-Pressure Rise Through a Short Diffuser
- Supplementary Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane with External Stores Installed: TED No. NACA DE 2393
- Hinge-Moment and Other Aerodynamic Characteristics at Transonic Speeds of a Quarter-Span Spoiler on a Tapered 45 Degree Sweptback Wing of Aspect Ratio 3
- Investigation of an NACA Submerged Inlet at Mach Numbers from 1.17 to 1.99
- Observations of Unsteady Flow Phenomena for an Inclined Body Fitted with Stabilizing Fins
- Tests at Mach Number 1.62 of a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces
- The Forces and Pressure Distribution at Subsonic Speeds on a Cambered and Twisted Wing Having 45 Degrees of Sweepback and Aspect Ratio of 3 and a Taper Ratio of 0.5
- Small-Scale Transonic Investigation of the Effects of Full-Span and Partial-Leading-Edge Flaps on the Aerodynamic Characteristics of a 50 Degree 38 Foot Sweptback Wing of Aspect Ratio 2.98
- On the Application of Transonic Similarity Rules to Wings of Finite Span
- An Investigation at Mach Numbers of 1.62 and 1.93 of the Lift Effectiveness and Integrated Downwash Characteristics of Several In-Line Missile Configurations Having Equal-Span Wings and Tails
- Control Hinge-Moment and Effectiveness Characteristics of a 60 Degree Half-Delta Tip Control on a 60 Degree Delta Wing at Mach Numbers of 1.41 and 1.96
- Downwash and Sidewash Fields Behind Cruciform Wings
- Preliminary Investigation of Cyclic De-Icing of an Airfoil Using an External Electric Heater
- Preliminary Results of Cyclical De-Icing of a Gas-Heated Airfoil
- First Landing of Bell X-2 Research Airplane
- Total-Pressure-Recovery Characteristics of a Model of the McDonnell XF3H-1 Inlets and Forebody in a Free Jet at a Mach Number of 1.55
- Wind-Tunnel Investigation of the Aerodynamic Characteristics of a 0.07-Scale Model of the North American MX-770 Missile
- A Wind-Tunnel Investigation of the Stability of the Antisubmarine Rocket Mk 1 Mod 0
- An Investigation Utilizing an Electrical Analogue of Cyclic Deicing of a Hollow Steel Propeller with an External Blade Shoe
- Impingement of Cloud Droplets on a Cylinder and Procedure for Measuring Liquid-Water Content and Droplet Sizes in Supercooled Clouds by Rotating Multicylinder Method