Browse TRAIL Inventories

Measurements of Aerodynamic Characteristics of a 35 Degree Sweepback NACA 65-009 Airfoil Model With 1/4 Chord Flap Having 31 Percent Flap Chord Overhang Balance by the NACA Wing Flow Method

Investigation of the Dynamic Longitudinal Stability of Two Equal Size Models Coupled in Tandem with a Single Joint: Preliminary Model Flight Tests

Investigation of Operating Pressure Ratio of a Supersonic Wind Tunnel Utilizing Distributed Boundary-Layer Suction in Test Section

An Investigation of the Longitudinal Characteristics of the X-3 Configuration Using Rocket-Propelled Models: Preliminary Results at Mach Numbers From 0.65 to 1.25

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Low-Speed Stalling and Lift Characteristics

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of the Buffet Boundary and Peak Airplane Normal-Force Coefficients at Mach Numbers Up to 0.90

Flight Tests at Supersonic Speeds to Determine the Effect of Taper on the Zero-Lift Drag of Sweptback Low-Aspect-Ratio Wings

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Static Lateral and Directional Stability Characteristics as Measured in Sideslips at Mach Numbers Up to 0.87

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Measurements of Wing Loads at Mach Numbers Up to 0.87

Flight Measurements With the Douglas D-558-II (BuAero No. 37974) Research Airplane: Lateral Control Characteristics as Measured in Abrupt Aileron Rolls at Mach Numbers Up to 0.86

Flight Measurements of the Pressure Distribution on the Wing of the X-1 Airplane (10 Percent Thick Wing) Over a Chordwise Station Near the Midspan, in Level Flight at Mach Numbers From 0.79 to 1.00 and in a Pull Up at a Mach Number of 0.98

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Lateral Control Characteristics at Mach Numbers of 1.40 and 1.59

Investigation of a Shrouded and an Unshrouded Axial-Flow Supersonic Compressor

Investigation at Mach Number 1.62 of the Pressure Distribution Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap

Investigation of a 42.7 Degree Sweptback Wing Model to Determine the Effects of Trailing-Edge Thickness on the Aileron Hinge-Moment and Flutter Characteristics at Transonic Speeds

Experimental Investigation of Spreading Characteristics of Choked Jets Expanding into Quiescent Air

Rough-Water Tests of Models of the Vosper and Plum Planing Boats

Preliminary Results From Fatigue Tests With Reference to Operational Statistics

Equations of Motion of a Rocket

Two-Dimensional Symmetrical Inlets With External Compression

Range Performance of Bombers Powered by Turbine-Propeller Power Plants

Time Histories of Horizontal-Tail Loads, Elevator Loads, and Deformations on a Jet-Powered Bomber Airplane During Abrupt Pitching Maneuvers at Approximately 20,000 Feet

Vibration of a Wing of Finite Span in a Supersonic Flow

Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Several Combinations of the Tail With Each of Two Foreshortened Body Segments

A Wind-Tunnel Investigation of the Effects of Thrust-Axis Inclination on Propeller First-Order Vibration

Investigation of the Model Me 210 in the Spin Wind Tunnel of the DVL: Fourth Partial Report - Model With Long Fuselage and With a Vee Tail

The Zero-Lift Drag of Several Configurations of the XAAM-N-2 Pilotless Aircraft, TED No. NACA DE332

Subsonic Gas Flow Past A Wing Profile

Tests of a Hermes A-2 Missile Body at Mach Number 4.04

Preliminary Results Obtained from Flight Test of a Rocket Model Having the Tail Only of the Grumman XF10F Airplane Configuration, TED No. NACA DE 354

Summary of Investigations of Mark 25 Aerial-Torpedo Turbine

Exact Solutions of Equations of Gas Dynamics

Hydrodynamic Properties of Planing Surfaces and Flying Boats

The Boundary Layers in Fluids with Little Friction

The Effect of the Inlet Mach Number and Inlet-Boundary-Layer Thickness on the Performance of a 23 Degree Conical-Diffuser-Tail-Pipe Combination

Annual Report of the National Advisory Committee for Aeronautics (33rd). Administrative Report Including Technical Report Nos. 863 to 891

Dynamic Response of Control Servo System Installed in NAES-Equipped SB2C-5 Airplane (BuAer No. 83135)

Ditching Investigation of a 1/10-Scale Model of the Grumman F9F-2 Airplane, TED No. NACA DE 335

Ditching Investigation of a 1/15-Scale Model of the Convair-Liner Airplane

Ditching Investigation of a 1/14-Scale Model of the Northrop C-125 Airplane

Investigation of the Spin and Recovery Characteristics of a 0.057-Scale Model of the Modified Chance Vought XF7U-1 Airplane. TED No. NACA DE 311

Free-Spinning-Tunnel Investigation of a 1/24-Scale Model of the Grumman AF-2S, -2W Airplane

Free-Spinning-Tunnel Investigation of a 1/30-Scale Model of the Grumman XF10F-1 Airplane

Instrument for Measuring the Wall Shearing Stress of Turbulent Boundary Layers

Investigations of Lateral Stability of a Glide Bomb Using Automatic Control Having No Time Lag

Investigations of the Wall-Shearing Stress in Turbulent Boundary Layers

An Investigation of the Longitudinal Characteristics of the MX-656 Configuration Using Rocket-Propelled Models Preliminary Results at Mach Numbers from 0.65 to 1.25

Some Studies on the Flow of a Gas in the Region of Transition Through the Velocity of Sound

Theoretical Investigations on the Efficiency and the Conditions for the Realization of Jet Engines

Wind-Tunnel Investigation of a Full-Scale Model of the Hughes MX-904 Missile


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