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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


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