Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
14045 results returnedSearch results
- Investigation of an Air-Cooled, Plug-Type, Variable-Area Exhaust Nozzle
- Investigation of an Underslung Normal-Wedge Inlet at Free-Stream Mach Numbers From 1.50 to 1.99
- Investigation of an Underslung Scoop Inlet at Mach Numbers to 1.99
- Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06
- Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Several Mach Numbers and Simulated Altitudes
- Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine
- Heat Transfer in Regions of Separated and Reattached Flows
- In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System
- Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0
- Investigation of Static Pressures and Boundary-Layer Characteristics on the Forward Parts of Nine Fuselages of Various Cross-Sectional Shapes at M Infinity Equal 2.01
- Analysis of Fluorine Addition to the Vanguard First Stage
- Brief Studies of Turbojet Combustor and Fuel-System Operation With Hydrogen Fuel at -400 Degrees F
- Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61
- Simplified Theory for Dynamic Relation of Ramjet Pressures and Fuel Flow
- Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations
- Thermal Stability of a Commercial Propyl Pentaborane (HEF-2) in the Range 147 Degree to 190 Degree C
- A Summary of the Longitudinal and Lateral Stability and Control Characteristics Obtained From Rocket-Model Tests of a Swept-Wing Fighter-Type Airplane at Mach Numbers From 0.5 to 1.9
- Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2
- Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01
- Total-Pressure Distortion and Recovery of Supersonic Nose Inlet With Conical Centerbody in Subsonic Icing Conditions
- Preliminary Investigation of Dynamic Lateral Stability Characteristics of a Configuration of the North American X-15 Research Airplane
- Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane
- Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power
- Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration
- Flutter Experiments With Various Control Configurations
- Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control
- Effects of Free-Stream Reynolds Number, Engine Installation, and Model Scale on Stability Characteristics of a Translating-Spike Inlet at Mach 2.0
- Heat-Exchanger-Core Weights for Use With Hydrogen-Expansion Turbine
- Hydrogen for Turbojet and Ramjet Powered Flight
- Experimental Evaluation of Swirl Can Elements for Hydrogen Fuel Combustor
- Performance and Operational Characteristics of Pentaborane Fuel in 48-Inch-Diameter Ram-Jet Engine
- Wind-Tunnel Investigation of a Wing-Root Inlet Configuration With Various Modifications at Mach Numbers of 1.41, 1.81, and 2.01
- Origin and Prevention of Crash Fires in Turbojet Aircraft
- Performance Evaluation of Reduced-Chord Rotor Blading as Applied to J73 Two-Stage Turbine
- Steady Nuclear Combustion in Rockets
- Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Missile Model During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination
- The Principles of Turbulent Heat Transfer
- Wind-Tunnel Investigation of the Republic F-105 Inlet with Various Modifications at Mach Numbers 1.41, 1.81, and 2.01
- On the Use of the Harmonic Linearization Method in the Automatic Control Theory
- Annual Report of the National Advisory Committee for Aeronautics (41st). Administrative Report Including Technical Report Nos. 1210 to 1253
- NACA Zero Power Reactor Facility Hazards Summary
- Preliminary Note on a Correlation of a Boundary-Layer Transition Results on Highly Cooled Blunt Bodies
- Heat of Combustion of the Product Formed by the Reaction of Acetylene, Ethylene, and Diborane
- Effect of Some External Crosswise Stiffeners on the Heat Transfer and Pressure Distribution on a Flat Plate at Mach Numbers of 0.77, 1.39, and 1.98
- Concluding Report of Free-Spinning, Tumbling, and Recovery Characteristics of a 1/18-Scale Model of the Ryan X-13 Airplane, Coord. No. AF-199
- Aerodynamic Forces on a Vibrating Unstaggered Cascade
- Measurements of Heat Transfer and Boundary-Layer Transition on an 8-Inch-Diameter Hemisphere-Cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88
- On the Spectrum of Natural Oscillations of Two-Dimensional Laminar Flows
- Reflection and Refraction of Acoustic Waves by a Shock Wave
- The Effect of Solid Admixtures on the Velocity of Motion of a Free Dusty Air Jet