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- High Mach Number, Low-Cowl-Drag, External-Compression Inlet With Subsonic Dump Diffuser
- Summary of Flight Data Obtained From 0.12-Scale Rocket-Powered Models of the Chance Vought Regulus 2 Missile
- Preliminary Transonic Flutter Investigation of Models of T-Tall of Blackburn NA-39 Airplane
- Some Notes on the Probable Damage to an Intercontinental-Ballistic-Missile Warhead Following Puncture of the Heat Shield
- A Wind Tunnel Investigation of Several Wingless Missile Configurations at Supersonic Speeds
- Experimental Study of Ballistic-Missile Base Heating with Operating Rocket
- Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.50
- Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives
- Stability of Ballistic Reentry Bodies
- A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds
- A Flight Evaluation and Analysis of the Effect of Icing Conditions on the ZPG-2 Airship
- Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet
- Effects of Surface Roughness and Extreme Cooling on Boundary-Layer Transition for 15 Degrees Cone-Cylinder in Free Flight at Mach Numbers to 7.6
- Droplet Impingement and Ingestion by Supersonic Nose Inlet in Subsonic Tunnel Conditions
- The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance
- An Investigation of the Performance of a Semielliptical Scoop Inlet at Mach Numbers of 1.60, 1.76, and 2.02
- Performance of Multiple Jet-Exit Installations
- Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight
- Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model
- Experimental Investigation of a 7-Inch-Tip-Diameter Transonic Turbine
- Exploratory Investigation of Performance of Experimental Fuel-Rich Hydrogen Combustion System
- Effect of Control Trailing-Edge Thickness or Aspect Ratio on the Oscillating Hinge-Moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds
- Experimental Investigation of a High Subsonic Mach Number Turbine Having a 40-Blade Rotor With Zero Suction-Surface Diffusion
- A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance
- Experimental Behavior of Pentaborane-Air Combustion Products During Expansion in a Convergent Divergent Nozzle
- Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Degree Swept- Wing-Fuselage Configuration at a Mach Number of 1.61
- Performance of a 28-Inch Ramjet Utilizing Gaseous Hydrogen at a Mach Number of 3.6, Angles of Attack Up to 12 Degrees, and Pressure Altitudes Up to 110,000 Feet
- Tracking Performance of a Swept-Wing Fighter With a Director-Type Radar Fire-Control System and Scope Presentation
- Boundary-Layer-Transition Measurements in Full-Scale Flight
- Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane
- Comparison of Injectors With a 200-Pound-Thrust Ammonia-Oxygen Engine
- Design and Experimental Investigation of a Single-Stage Turbine With a Rotor Entering Relative Mach Number of 2
- Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58
- Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude
- Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls
- Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53
- Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls
- Maneuver Performance of Interceptor Missiles
- An Investigation of the Effect of Target Temperature on Projectile Penetration and Cratering
- Investigation of Control Signals for Variable Ramps of Twin-Duct Side Inlets
- Hydrodynamic Characteristics of Missiles Launched Under Water
- Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane
- Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
- Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane
- Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
- Effect of Dissociation on Exhaust-Nozzle Performance
- Experimental and Analytical Investigation of the Transonic and Supersonic Divergence Characteristics of a Delta-Plan-Form All-Movable Control
- An Experimental Investigation of the Static Longitudinal Stability and Control Characteristics of a Wingless Missile Configuration at Mach Numbers From 3.0 to 6.3
- Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51
- Investigation of an All-Movable Control Surface at a Mach Number of 6.86 for Possible Flutter