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- Analysis of Wind-Tunnel Tests to a Mach Number of 0.90 of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10
- Aerodynamic Loads on an External Store Adjacent to an Unswept Wing at Mach Numbers Between 0.75 and 1.96
- Longitudinal Stability Investigation for a Mach Number Range of 0.8 to 1.7 of an Airplane Configuration With a 45 Degree Swept Wing and a Low Horizontal Tail
- Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2
- Method for Calculating Effects of Dissociation on Flow Variables in the Relaxation Zone Behind Normal Shock Waves
- Longitudinal Stability Characteristics of a Simple Infrared Homing Missile Configuration at Mach Numbers of 0.7 to 1.4
- Investigation of Jet Effects on a Flat Surface Downstream of the Exit of a Simulated Turbojet Nacelle at a Free-Stream Mach Number of 1.39
- Method for Shortening Ram-Jet Engines by Burning Hydrogen Fuel in the Subsonic Diffuser
- Flight Investigation of the Effect of a Propulsive Jet Positioned According to the Transonic Area Rule on the Drag Coefficients of a Single-Engine Delta-Wing Configuration at Mach Numbers From 0.83 to 1.36
- A Flight Investigation of the Handling Characteristics of a Fighter Airplane Controlled Through a Rate Type of Automatic Control System
- A Flight Investigation of the Handling Characteristics of a Fighter Airplane Controlled Through an Attitude Type of Automatic Pilot
- Flight Investigation of Factors Affecting Pilots' Ability to Utilize a Radarscope Display of Steering Information
- Heat Transfer on the Lifting Surfaces of a 60 Degree Delta Wing at Angle of Attack for Mach Number 1.98
- Investigation of the Use of Area Suction to Increase the Effectiveness of Trailing-Edge Flaps of Various Spans on a Wing of 45 Degree Sweepback and Aspect Ratio 6
- Investigation to Determine Effects of Center-of-Gravity Location on the Transonic Flutter Characteristics of a 45 Degree Sweptback Wing
- A Low-Speed Investigation of a High-Lift Lateral-Control Device Consisting of a Spoiler-Slot-Deflector and a Trailing-Edge Flap on a Tapered 45 Degree Sweptback Wing
- Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 10 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.9
- Investigation of the Ejection Release of Several Dynamically Scaled Bluff Internal Stores at Mach Numbers of 0.8, 1.39, and 1.98
- Lateral Stability and Control Measurements of a Fighter-Type Airplane With a Low-Aspect-Ratio Unswept Wing and a Tee-Tail
- Lateral Stability Characteristics Between Mach Numbers of 0.80 and 1.57 and Simulation of Coupled Motion at Mach Number of 1.30 of a Rocket-Propelled Model of an Airplane Configuration Having Thin Highly Tapered 45 Degree Sweptback Surfaces
- Large Deflection of Curved Plates
- Heat Transfer and Pressure Distribution at a Mach Number of 6.8 on Bodies With Conical Flares and Extensive Flow Separation
- Free-Flight Flutter Tests in the Transonic and Low Supersonic Speed Range of Three Low-Aspect-Ratio Swept, Tapered Wings on Rocket-Propelled Vehicles
- Free-Flight Aerodynamic-Heating Data to Mach Number 10.4 for a Modified Von Karman Nose Shape
- Flight Measurements of Section Efficiency, Thrust, and Power of a Supersonic-Type Propeller at Mach Numbers to 0.9
- Flight Test of a Solid-Fuel Ram Jet With the Internal Surface of the Combustor Air Cooled
- Flight Measurements of the Vibratory Bending and Torsion Stress of a Supersonic-Type Propeller for Flight Mach Numbers Up to 0.95
- Force and Pressure-Distribution Measurements at a Mach Number of 3.12 of Slender Bodies Having Circular, Elliptical, and Triangular Cross Sections and the Same Longitudinal Distribution of Cross-Sectional Area
- Flutter of Thin Propeller Blades, Including Effects of Mach Number, Structural Damping, and Vibratory-Stress Measurements Near the Flutter Boundaries
- Investigation at Transonic Speeds of the Effects of Inlet Lip Stagger on the Internal-Flow Characteristics of an Unswept Semielliptical Air Inlet
- Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Static Longitudinal Stability and Control and Performance Characteristics at Transonic Speeds
- Investigation at Supersonic Speeds of the Variation With Reynolds Number and Mach Number of the Total, Base, and Skin-Friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag
- The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10
- A Wind-Tunnel Investigation of the Effect of Nose Ring Spoilers on a Low-Speed Slowly Spinning Fin-Stabilized Rocket
- Flight Tests of Fifteen T-231 Gun-Launched Rocket Projectiles
- The Accuracy of the Substitute-Stringer Approach for Determining the Bending Frequencies of Multistringer Box Beams
- Analysis of a spin and recovery from time histories of attitudes and velocities as determined for a dynamic model of a contemporary fighter airplane in the free-spinning tunnel
- Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds
- Aerodynamic investigation of a parabolic body of revolution at Mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base
- Aerodynamic mixing downstream from line source of heat in high-intensity sound field
- An air-flow-direction pickup suitable for telemetering use on pilotless aircraft
- An analysis of airspeed, altitude, and acceleration data obtained from a twin-engine transport airplane operated over a feeder-line route in the Rocky Mountains
- An analysis of buzzing in supersonic ram jets by a modified one-dimensional nonstationary wave theory
- Analysis and comparison with theory of flow-field measurements near a lifting rotor in the Langley full-scale tunnel
- Experimental investigation of air-cooled turbine rotor blade temperatures in a turbojet engine operating at turbine-inlet temperatures up to 2580 R and altitudes of 50,000 and 60,000 feet
- Experimental investigation on the Langley helicopter test tower of compressibility effects on a rotor having NACA 63₂-015 airfoil sections
- Effects of wing-tip droop on the longitudinal characteristics of two highly swept wing-body combinations at Mach numbers from 0.6 to 1.4
- A buffet investigation at high subsonic speeds of wing-fuselage-tail combinations having sweptback wings with NACA 64A thickness distributions, fences, a leading-edge extension, and body contouring
- A study of liquid boric oxide particle growth rates in a gas stream from a simulated jet engine combustor
- Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas