TRAIL - Technical Report Archive and Image Library

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

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