Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
14045 results returnedSearch results
- Flight Measurements of the Vibratory Bending and Torsional Stresses on a Modified Supersonic Propeller for Forward Mach Numbers up to 0.95
- Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines
- Performance of Basic XJ79-GE-1 Turbojet Engine and Its Components
- Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14
- Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations
- Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines
- Preliminary Analysis of Hydrogen-Rich Hypersonic Ramjet Operation
- Off-Design Performance of Divergent Ejectors
- Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
- Performance of Five Short Multielement Turbojet Combustors for Hydrogen Fuel in Quarter-Annulus Duct
- A Preliminary Study of the Effect of Boric Oxide Deposits on the Performance of Two Selected Turbine Stator-Blade Shapes
- Flight, Analog-Simulator, and Analytical Studies of an Automatically Controlled Interceptor Which Uses a Bank-Angle-Error Computer for Lateral Commands
- Some Effects of Reynolds Number on the Stability of a Series of Flared-Body and Blunted-Cone Models at Mach Numbers From 1.62 to 6.86
- Some Experimental Heating Data on Convex and Concave Hemispherical Nose Shapes and Hemispherical Depressions on a 30-Degree Blunted Nose Cone
- Survey of Supersonic Inlets for High Mach Number Applications
- 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