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- Effect of Wedge-Type Boundary-Layer Diverters on Performance of Half-Conical Side Inlets at Mach Number 2.96
- Effect on Transonic and Supersonic Drag of a Fuselage Protuberance of an Essential Unswept Wing-Fuselage Combination
- The Effect of Canopy Location on the Aerodynamic Characteristics of a Sweptback Wing-Body Configuration at Transonic Speeds
- Effects of a Series of Inboard Plan-Form Modifications on the Longitudinal Characteristics of Two Unswept Wings of Aspect Ratio 3.5, Taper Ratio 0.2, and Different Thickness Distributions at Mach Numbers of 1.61 and 2.01
- Effect of Nozzle Secondary Flows on Turbine Performance as Indicated by Exit Surveys of a Rotor
- The Effects of Operating Propellers on the Longitudinal Characteristics at High Subsonic Speeds of a Four-Engine Tractor Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10
- Effects of Canopy, Revised Vertical Tail, and a Yaw-Damper Vane on the Aerodynamic Characteristics of a 1/16-Scale Model of the Douglas D-558-II Research Airplane at a Mach Number of 2.01
- The Effects of Changes in Aspect Ratio and Tail Height on the Longitudinal Stability Characteristics at High Subsonic Speeds of a Model With a Wing Having 32.6 Degree Sweepback
- Effects of Auxiliary and Ejector Pumping on the Mach Number Attainable in a 4 1/2- by 4 1/2-Inch Slotted Tunnel at Low Pressure Ratios
- Dynamic Stability and Control Characteristics of a Ducted-Fan Model in Hovering Flight
- Determination of Longitudinal Stability in Supersonic Accelerated Maneuvers for the Douglas D-558-II Research Airplane
- Drag and Heat Transfer on a Parabolic Body of Revolution (NACA RM-10) in Free Flight to Mach Number 2 With Both Constant and Varying Reynolds Number and Heating Effects on Turbulent Skin Friction
- Drag Measurements on a 1/6-Scale, Finless, Sting-Mounted NACA RM-10 Missile in Flight at Mach Numbers From 1.1 to 4.04 Showing Some Reynolds Number and Heating Effects
- The Effect of an Operating Propeller on the Aerodynamic Characteristics at High Subsonic Speeds of a Model of a Vertical-Rising Airplane Having an Unswept Wing of Aspect Ratio 3
- Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil With Partical-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection
- Comparison of Wind-Tunnel, Rocket, and Flight Drag Measurements for Eight Airplane Configurations at Mach Numbers Between 0.7 and 1.6
- Calculated Effect of Uranium Distribution on Reflector Control Effectiveness for a Water-Moderated Power Reactor
- Analysis of Wind-Tunnel Tests at Low Speeds of a Four-Engine Propeller-Driven Airplane Configuration Having a Wing With 40 Degrees of Sweepback
- Analytical Study of the Effect of Center-of-Gravity Position on the Response to Longitudinal Control in Landing Approaches of a Swept-Wing Airplane of Low Aspect Ratio Having No Horizontal Tail
- Measured and Estimated Lateral Static and Rotary Derivatives of a 1/12-Scale Model of a High-Speed Fighter Airplane With Unswept Wings
- Low-Amplitude Damping-in-Pitch Characteristics of Four Tailless Swept Wing-Body Combinations at Mach Numbers From 0.85 to 1.30 as Obtained With Rocket-Powered Models
- Longitudinal Stability Characteristics at Transonic Speeds of a Canard Configuration Having a 45 Degree Sweptback Wing of Aspect Ratio 6.0 and NACA 65A009 Airfoil Section
- Low-Amplitude Damping-in-Pitch Characteristics of Tailless Delta-Wing-Body Combinations at Mach Numbers From 0.80 to 1.35 as Obtained With Rocket-Powered Models
- Low-Speed Investigation of the Effects of Location of a Delta and a Straight Tail on the Longitudinal Stability and Control of a Thin Delta Wing With Extended Double Slotted Flaps
- Investigation of Mechanical Fastenings for Solid Turbine Blades Made From Ductile Materials
- An Investigation of Effects of Flame-Holder Gutter Shape on Afterburner Performance
- Investigation of a Transonic Turbine Designed for a Maximum Rotor-Blade Suction-Surface Relative Mach Number of 1.57
- Investigation of Adjustable Supersonic Inlet in Combination With J34 Engine Up to Mach 2.0
- Flight Investigation of the Rolling Effectiveness of Fingered Semaphore Spoilers on a Tapered 45 Sweptback Wing Between Mach Numbers 0.6 and 1.3
- Flight Investigation to Determine Lift and Drag Characteristics of a Canard Ram-Jet Missile Configuration in the Mach Number Range of 0.8 to 2.0
- A Flight Investigation of the Effects of Inclination of the Principal Axis of Inertia on the Dynamic Lateral Stability of the Republic XF-91 Airplane
- Flight Investigation of the Aerodynamic Derivatives and Performance of Control Systems of Two Full-Scale Guided Bombs
- Flight Investigation of Engine Nacelles and Wing Vertical Position on the Drag of a Delta-Wing Airplane Configuration Form Mach Number 0.8 to 2.0
- The Hydrodynamic Planing Lift of Four Surfaces as Measured in a 200-FPS Free Jet
- Investigation of the Normal Force Accompanying Thrust-Axis Inclination of the NACA 1.167-(0)(03)-058 and the NACA 1.167-(0)(05)-058 Three-Blade Propellers at Forward Mach Numbers to 0.90
- Longitudinal Stability and Drag Characteristics of a Fin Stabilized Body of Revolution With a Fineness Ratio of 12 as Measured by the Free-Fall Method
- Low-Speed Cascade Tests of Two 45 Degree Swept Compressor Blades With Constant Spanwise Loading
- Low-Speed Chordwise Pressure Distributions Near the Midspan Station of the Slotted Flap and Aileron of a 1/4-Scale Model of the Bell X-1 Airplane With a 4-Percent-Thick, Aspect-Ratio-4, Unswept Wing
- Measurement and Calculation of Blade Torsional Deflection of Three Supersonic-Type Propellers
- Measured Data Pertaining to Buffeting at Supersonic Speeds of the Douglas D-558-II Research Airplane
- Measurements and Predictions of Flow Conditions on a Two-Dimensional Base Separating a Mach Number 3.36 Jet and a Mach Number 1.55 Outer Stream
- Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double-Wedge Sections With the Maximum Thickness at 0.18 Chord
- Investigation of the Effect of Balancing Tabs on the Hinge-Moment Characteristics of a Trailing-Edge Flap-Type Control on a Trapezoidal Wing at a Mach Number of 1.61
- Investigation of the Effect of Indentation on an M-Plan-Form-Wing--Body Combination at Transonic Speeds
- An Investigation of the Characteristics of the NACA RM-10 (With and Without Fins) in the Langley 11-Inch Hypersonic Tunnel at a Mach Number of 6.9
- Experimental Effects of Propulsive Jets and Afterbody Configurations on the Zero-Lift Drag of Bodies of Revolution at a Mach Number of 1.59
- Hinge-Moment, Lift, and Pitching-Moment Characteristics of a Flap-Type Control Surface Having Various Hinge-Line Locations on a 4-Percent-Thick 60 Degree Delta Wing: Transonic Bump Method
- Flight Tests of a Man Standing on a Platform Supported by a Teetering Rotor
- Investigation at Transonic Speeds of the Lateral-Control and Hinge-Moment Characteristics of a Flap-Type Spoiler Aileron on a 60 Degree Delta Wing
- An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Stability and Control Characteristics at a Mach Number of 1.61 of the Complete Configuration Equipped With Spoilers