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- Temperature Drops Through Liquid-Cooled Turbine Blades With Various Cooling-Passage Geometries
- Tensile Properties of HK31XA-H24 Magnesium-Alloy Sheet Under Rapid-Heating Conditions and Constant Elevated Temperatures
- Tentative Method for Calculation of the Sound Field About a Source Over Ground Considering Diffraction and Scattering Into Shadow Zones
- Experimental Investigation of the Strength of Multiweb Beams With Corrugated Webs
- Influence of Copper Ions on Adherence of Vitreous Coatings to Stainless Steel
- Experimental Study and Analysis of Loading and Pressure Distributions on Delta Wings Due to Thickness and to Angle of Attack at Supersonic Speeds
- An Experimental Study at High Subsonic Speeds of Several Tail Configurations on a Model with an Unswept Wing
- Influence of Hot-Working Conditions on High-Temperature Properties of a Heat-Resistant Alloy
- Effect of Design Over-All Compressor Pressure Ratio Division on Acceleration Characteristics of Three Hypothetical Two-Spool Turbojet Engines
- Mechanical Tests on Specimens From Large Aluminum-Alloy Forgings
- Evaluation of Liquefied Hydrocarbon Gases as Turbojet Fuels
- Low-Speed Longitudinal Aerodynamic Characteristics of a 45 Degree Sweptback Wing With Double Slotted Flaps
- An Investigation of Ejection Releases of Submerged and Semisubmerged Dynamically Scaled Stores from a Simulated Bomb Bay of a Fighter-Bomber Airplane at Supersonic Speeds
- Factors Controlling Air-Inlet Flow Distortions
- Characteristics of Four Nose Inlets as Measured at Mach Numbers Between 1.4 and 2.0
- Experimental Investigation of a Transonic Axial-Flow-Compressor Rotor Designed for Sonic Inlet Velocity with an Inlet Hub-Tip Radius of 0.35
- Transonic-Wind-Tunnel Investigation of the Effects of Lip Bluntness and Shape on the Drag and Pressure Recovery of a Normal-Shock Nose Inlet in a Body of Revolution
- Investigation of the Laminar Aerodynamic Heat-Transfer Characteristics of a Hemisphere-Cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8
- Effect of a Fuselage on the Low-Speed Longitudinal Aerodynamic Characteristics of a 45 Degree Sweptback Wing with Double Slotted Flaps
- Time-Vector Determined Lateral Derivatives of a Swept-Wing Fighter-Type Airplane with Three Different Vertical Tails at Mach Numbers Between 0.70 and 1.48
- Study of Aluminum Deformation by Electron Microscopy
- Analysis of Limitations Imposed on One-Spool Turboprop-Engine Designs by Compressors and Turbines at Flight Mach Numbers of 0.06, and 0.8
- Preliminary Investigation of a Family of Diffusers Designed for Near Sonic Inlet Velocities
- Effect of Mach Number on Boundary-Layer Transition in the Presence of Pressure Rise and Surface Roughness on an Ogive-Cylinder Body with Cold Wall Conditions
- Performance and Operational Studies of a Full-Scale Jet-Engine Thrust Reverser
- Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 3: Effect of Tip Taper on Over-All and Blade-Element Performances
- A Theoretical Estimate of the Effects of Compressibility on the Performance of a Helicopter Rotor in Various Flight Conditions
- Mach Number Measurements and Calibrations During Flight at High Speeds and at High Altitudes Including Data for the D-558-II Research Airplane
- An Investigation of the Release Characteristics of a 1/30 Dynamically Scaled AVCO Booster Vehicle from the Simulated Bomb Bay of the B-52 Airplane : COORD. No. AF-AM-59
- Experimental Investigation of a Five-Stage Axial-Flow Research Compressor With Transonic Rotors in All Stages 3: Interstage Data and Individual Stage Performance Characteristics
- Transonic Wind-Tunnel Investigation of the Aerodynamic Loading Characteristics of a Highly Tapered Upswept Wing in the Presence of a Body With and Without Indentation
- Limited Hydrodynamic Investigation of a 1/15-Size Model of a Modified Nose-Inlet Multijet Water-Based Aircraft
- Pressure Distributions at Mach Numbers of 1.6 and 1.9 of a Conically Cambered Wing of Triangular Plan Form With and Without Pylon-Mounted Engine Nacelles
- On the Range of Applicability of the Transonic Area Rule
- Fabrication Techniques and Heat-Transfer Results for Cast-Cored Air-Cooled Turbine Blades
- Comparison of Performance and Component Frontal Areas of Hypothetical Two-Spool and One-Spool Turbojet Engines
- Effect of Ambient Conditions on the Performance of a Pressure-Jet Powerplant for a Helicopter
- Performance Analysis of Fixed- and Free-Turbine Helicopter Engines
- Hinge Moment and Effectiveness of an Unswept Constant-Chord Control and an Overhang-Balanced, Swept Hinge-Line Control on an 80 Degree Swept Pointed Wing at Mach Numbers from 0.75 to 1.96
- Failure Characteristics of Pressurized Stiffened Cylinders
- Performance of a Double-Ramp Side Inlet With Combinations of Fuselage, Ramp, and Throat Boundary-Layer Removal, Mach Number Range, 1.5 to 2.0
- Performance of Pentaborane, Pentaborane - JP-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-scale Turbojet Engine
- Performance of Several Half-Conical Side Inlets at Supersonic and Subsonic Speeds
- Performance of Variable Two-Dimensional Inlet Designed for Engine-Inlet Matching 1 - Performance at Design Mach Number of 3.07
- Some Effects of Roll Rate on the Longitudinal Stability Characteristics of a Cruciform Missile Configuration as Determined From Flight Test for a Mach Number Range of 1.1 to 1.8
- Some Transonic Aerodynamic Characteristics of a Model Similar to the McDonnell F3H-2N Airplane
- Static Lateral and Directional Stability and Control Characteristics of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01
- Preliminary Report on Experimental Investigation of Engine Dynamics and Controls for a 48-Inch Ramjet Engine
- Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 1/20-Scale Model of the McDonnell F4H-1 Airplane at Mach Numbers of 1.59, 1.89, and 2.09
- Surge-Inception Study in a Two-Spool Turbojet Engine