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- 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
- Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile With Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51
- Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87
- Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials
- A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile
- Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10
- Free-Flight Aerodynamic-Heating Data at Mach Numbers Up to 10.9 on a Flat-Faced Cylinder
- Heat-Transfer Measurements on a Concave Hemispherical Nose Shape With Unsteady-Flow Effects at Mach Numbers of 1.98 and 4.95
- Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0
- An Investigation of Supersonic Store Interference in the Vicinity of a 22 Degree Swept Wing Fuselage Configuration at Mach Numbers of 1.61 and 2.01
- Buffet Tests of an Attack-Airplane Model With Emphasis on Analysis of Data From Wind-Tunnel Tests
- Dynamic Lateral Behavior of High-Performance Aircraft
- Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel
- Performance of JP-4 Fuel With Fluorine-Oxygen Mixtures in 1000-Pound-Thrust Rocket Engines
- Static Stability and Control of Hypersonic Gliders
- A Preliminary Investigation of the Performance of a Short Length Turbojet Combustor Using Vaporized Hydrocarbon Fuels
- Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane
- Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree Cone-Cylinder-Flare Configuration at Mach Numbers Up to 9.89
- Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane
- Heat-Transfer and Pressure Measurements From a Flight Test of the Second 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.91 and Reynolds Number Per Foot of 23.4 by 10 to the 6th Power
- An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control
- A Comparison of Flight-Measured Carrier- Approach Speeds With Values Predicted by Several Different Criteria for 41 Fighter-Type Airplane Configurations
- An Analog Study of the Influence of Internal Modifications to a Wing Leading Edge on Its Transient Temperature Rise During Highspeed Flight
- Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18
- Comparison of Various Heat Exchangers for Liquid-Metal Nuclear Turbojet Over Range of Flight and Operating Conditions
- Turbine Engines for High-Speed Flight
- Experimental Investigation of Extreme Internal Flow Turning at the Cowl Lip of an Axisymetric Inlet at a Mach Number of 2.95
- Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model
- Some Effects of Rapid Inlet Pressure Oscillation on the Operation of a Turbojet Engine
- Transonic-Wind-Tunnel Tests of the Aerodynamic Characteristics of a 0.15-Scale Model of the North American Aviation 255-Inch Fin-Stabilized External Store, Coord No. AF-AM-4
- Investigation of a Prototype Iroquois Turbojet Engine in an Altitude Test Chamber Coord. No. AF-P-6
- The Interaction of a Reflected Shock Wave with the Boundary Layer in a Shock Tube
- Investigation of Aperiodic Time Processes With Autocorrelation and Fourier Analysis
- On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas
- On Possible Similarity Solutions for Three-Dimensional Incompressible Laminar Boundary-Layer Flows Over Developable Surfaces and with Proportional Mainstream Velocity Components
- Impact on a Compressible Fluid