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- Photographic Study of Rotary Screaming and Other Oscillations in a Rocket Engine
- Performance Characteristics of Several Full-Scale Double-Shroud Ejector Configurations Over a Range of Primary Gas Temperatures
- A Preliminary Investigation of the Pressure Recovery of Several Two-Dimensional Supersonic Inlets at Mach Number of 2.01
- Preliminary Investigation of the Performance of a Single Tubular Combustor at Pressure Up to 12 Atmospheres
- A Preliminary Flight Investigation of an Oil-Flow Technique for Air-Flow Visualization
- Experimental Investigation of the Damping in Roll of Cruciform Triangular Wing-Body Combinations at Mach Numbers From 1.5 to 6.0
- Exploratory Investigation of External Stores in the Aerodynamic Characteristics of a 1/16-Scale Model of the Douglas D-558-II Research Airplane at a Mach Number of 2.01
- Experimental Investigation of the Oscillating Forces and Moments on a Two-Dimensional Wing Equipped With an Oscillating Circular-Arc Spoiler
- Flight and Preflight Evaluation of an Automatic Thrust-Coefficient Control System in a Twin-Engine Ram-Jet Missile
- Flight-Determined Pressure Measurements Over the Wing of the Douglas D-558-II Research Airplane at Mach Numbers Up to 1.14
- Experimental Investigation of Rotating Stall and Blade Vibration in the Axial-Flow Compressor of a Turbojet Engine
- Flight Determination of the Buffeting Characteristics of the Bell X-5 Research Airplane at 58.7 Degrees Sweepback
- Stabilization of 50-Percent Magnesium - JP-4 Slurries With Some Aluminum Soaps of C(Sub 8) Acids
- Preliminary Report of Experimental Investigation of Ram-Jet Controls and Engine Dynamics
- Preliminary Investigation of the Flow in an Annular-Diffuser-Tailpipe Combination With an Abrupt Area Expansion and Suction, Injection, and Vortex-Generator Flow Controls
- Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbine for Turbojet Engines 1: Turbine Performance and Engine Weight-Flow Capacity
- Application of Radial-Equilibrium Condition to Axial-Flow Turbomachine Design Including Consideration of Change of Entropy With Radius Downstream of Blade Row
- Experimental Sea-Level Static Investigation of a Short Afterburner
- Transonic Aerodynamic and Loads Characteristics of a 4-Percent-Thick Unswept-Wing--Fuselage Combination
- The Effect of Nacelle Location on the Zero-Lift Drags of 45 Degree Sweptback Wing-Body Configurations Having Boattail and Cylindrical Afterbodies as Determined by Flight Tests at Transonic Speeds
- A Transonic Wind-Tunnel Investigation of the Longitudinal Force and Moment Characteristics of a Plane and a Cambered 3-Percent-Thick Delta Wing of Aspect Ratio 3 on a Slender Body
- A Transonic Wind-Tunnel Investigation of the Static Lateral, Directional, and Longitudinal Stability Characteristics of the Martin B-61A Missile (Matador)
- Transonic Flight Test of a Rocket-Powered Model to Determine Propulsive Jet Influence on the Configuration Drag
- Transonic Drag Measurements of Eight Body-Nose Shapes
- A Study of the Problem of Designing Airplanes With Satisfactory Inherent Damping of the Dutch Roll Oscillation
- Rocket-powered-model investigation of the hinge-moment and normal-force characteristics of a half-diamond tip control on a 60 degree sweptback diamond wind between Mach numbers of 0.5 and 1.3
- Rocket-Powered Model Investigation of Lift, Drag, and Stability of a Body-Tail Configuration at Mach Numbers From 0.8 to 2.3 and Angles of Attack Between Plus or Minus 6.5 Degrees
- Pressure Distributions on Plug- and Semaphore-Type Spoiler Ailerons on a 35 Degree Sweptback Wing of Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section at High Subsonic Speeds
- Pressures and Associated Aerodynamic and Load Characteristics for Two Bodies of Revolution at Transonic Speeds
- Pressure Recovery and Drag Characteristics of a Forward Located Circular Scoop Inlet as Determined From Flight Tests for Mach Numbers From 0.8 to 1.6
- Theoretical Investigation Based on Experimental Frequency-Response Measurements of an Automatic Altitude Control in Combination With Supersonic Missile Configuration
- The Use of Area Suction to Increase the Effectiveness of a Trailing-Edge Flap on a Triangular Wing of Aspect Ratio 2
- Variation of Spontaneous Ignition Delays With Temperature and Composition for Propane-Oxygen-Nitrogen Mixtures at Atmospheric Pressure
- Wind-Tunnel Investigation at High Subsonic Speeds of the Effects of Wing-Mounted External Stores on the Loading and Aerodynamic Characteristics in Pitch of a 45 Degree Sweptback Wing Combined With a Fuselage
- A Wind-Tunnel Investigation at High Subsonic Speeds of the Lateral Control Characteristics of Various Plain Spoiler Configurations on a 3-Percent-Thick 60 Degree Delta Wing
- Wind-Tunnel Investigation at High Subsonic Speeds of the Stability Characteristics of a Complete Model Having Sweptback-, M-, W-, and Cranked-Wing Plan Forms and Several Horizontal-Tail Locations
- Wind-Tunnel Investigation at Low and Transonic Speeds of the Feasibility of Self-Actuating Spoilers as a Lateral-Control Device for a Missile
- Transonic Wind-Tunnel Investigation of the Effects of Taper Ratio, Body Indentation, Fixed Transition, and Afterbody Shape on the Aerodynamic Characteristics of a 45 Degree Sweptback Wing-Body Combination
- Transonic Wind-Tunnel Investigation of the Effects of Body Indentation on the Aerodynamics of a Semielliptical Sweptback Wing-Root Inlet Configuration
- Wind-Tunnel Experiments Concerning the Dynamic Behavior of a Low-Speed Slowly Spinning Fin-Stabilized Rocket
- Zero-Lift Drag of the Chance Vought Regulus II Missile at Mach Numbers Between 0.8 and 2.2 as Determined From the Flight Tests of Two 0.12-Scale Models: TED No. NACA AD 398
- Zero-Lift Drag of Several Conical and Blunt Nose Shapes Obtained in Free Flight at Mach Numbers of 0.7 to 1.3
- Evaluation of a Silicone-Diester Lubricant in Bench Studies and in a Turbopropeller Engine
- A Summary of the Low-Lift Drag and Longitudinal Trim Characteristics of Two Versions of an Interceptor-Type Airplane as Determined From Flight Tests of Rocket-Powered Models at Mach Numbers Between 0.75 and 1.78
- Formulas for the Elastic Constants of Plates With Integral Waffle-Like Stiffening
- Investigation at Supersonic Speeds of the Effect of Jet Mach Number and Divergence Angle of the Nozzle Upon the Pressure of the Base Annulus of a Body of Revolution
- A Wind-Tunnel Investigation of the Use of Spoilers for Obtaining Static Longitudinal Stability of a Canard-Missile Model in Reverse Flight
- Design of Combustor for Long-Range Ram-Jet Engine and Performance of Rectangular Analog
- The Effect of Some Surface Roughness Elements on the Drag of a Body of Revolution at Supersonic Speeds
- Effect of Mechanically Induced Sinusoidal Air-Foil Oscillations on Operation of a Ram-Jet Engine