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- Charts Relating the Compressive and Shear Buckling Stresses of Longitudinally Supported Plates to the Effective Deflectional Stiffness
- Performance of a Two-Dimensional Cascade Inlet at a Free-Stream Mach Number of 3.05 and at Angles of Attack of -3 Degrees, 0 Degrees, 3 Degrees, and 6 Degrees
- Effects of Canard Surface Size on Stability and Control Characteristics of Two Canard Airplane Configuration at Mach Numbers of 1.41 and 2.01
- Handbook of Structural Stability Part 6: Strength of Stiffened Curved Plates and Shells
- High-Speed Hydrodynamic Characteristics of a Flat Plate and 20 Degrees Dead-Rise Surface in Unsymmetrical Planing Conditions
- Mass Transfer Cooling Near the Stagnation Point
- On Pairs of Solutions of a Class of Internal Viscous Flow Problems With Body Forces
- Ground Simulator Studies of a Small Side-Located Controller in a Power Control System
- Turbojet Engine Noise Reduction With Mixing Nozzle-Ejector Combinations
- Experimental Investigation of the Effect of Circumferential Inlet Flow Distortion on the Performance of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages
- Static Longitudinal and Lateral Stability Characteristics at Low Speed of 60 Degree Sweptback-Midwing Models Having Wings with an Aspect Ratio of 2, 4, or 6
- 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
- Compressive Strength and Creep of 17-7 PH Stainless-Steel Plates at Elevated Temperatures
- Second-Order Slender-Body Theory: Axisymmetric Flow
- Experimental Lift-Drag Ratios for Two Families of Wing-Body Combinations at Supersonic Speeds
- Transient Heating Effects on the Bending Strength of Integral Aluminum-Alloy Box Beams
- Effect of Temperature on Dynamic Modulus of Elasticity of Some Structural Alloys
- Measurements in a Shock Tube of Heat-Transfer Rates at the Stagnation Point of a 1.0-Inch-Diameter Sphere for Real-Gas Temperatures Up to 7,900 R
- An Approximate Method for Design or Analysis of Two-Dimensional Subsonic-Flow Passages
- Flight Investigation of a Full-Scale Aircraft Ejector with Various Spacing Ratios and Correlation with Small-Scale Tests
- Simulator Investigation of Command Reaction Controls
- The Effects of Body Vortices and the Wing Shock-Expansion Field on the Pitch-Up Characteristics of Supersonic Airplanes
- A Simulator Investigation of Factors Affecting the Design and Utilization of a Stick Pusher for the Prevention of Airplane Pitch-Up
- Lift and Moment on Thin Arrowhead Wings with Supersonic Edges Oscillating in Symmetric Flapping and Roll and Application to the Flutter of an All-Moveable Control Surface
- Tables and Graphs of Normal-Shock Parameters at Hypersonic Mach Numbers and Selected Altitudes
- Effect of Advance Ratio on Flight Performance of a Modified Supersonic Propeller
- On Fully Developed Channel Flows: Some Solutions and Limitations, and Effects of Compressibility, Variable Properties, and Body Forces
- Experimental Investigation of Distortion Removal Characteristics of Several Free-Wheeling Fans
- Wind-Tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack up to 13 Degrees and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives
- Some Static Longitudinal Stability Characteristics of an Overlapped-Type Tandem-Rotor Helicopter at Low Airspeeds
- Reflection and Transmission of Sound by a Slotted Wall Separating Two Moving Fluid Streams
- Investigation of the Performance and Internal Flow of a Variable-Area, Variable-Internal-Contraction Inlet at Mach Numbers of 2.00, 2.50, and 2.92
- Transonic Wind-Tunnel Investigation of the Effect of Horizontal Tail on Longitudinal Stability of Two 60 Degree Sweptback-Wing-Body Configurations with Aspect Ratios of 2.67 and 4.00
- Temperature-Pressure-Time Relations in a Closed Cryogenic Container
- Flight Measurements of the Vibratory Stresses on a Propeller Designed for an Advance Ratio of 4.0 and a Mach Number of 0.82
- 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