Browse TRAIL Inventories

Stresses in a Two-Bay Noncircular Cylinder Under Transverse Loads

Analysis of Fully Developed Turbulent Heat Transfer at Low Peclet Numbers in Smooth Tubes With Application to Liquid Metals

Gust-Tunnel Investigation of a Delta-Wing Model With the Leading Edge Swept Back 60 Degrees

Flow Separation From Rods Ahead of Blunt Noses at Mach Number 2.72

Free-Flight Investigation of the Zero-Lift Drag of Several Wings at Supersonic Mach Numbers Extending to 2.6

Flight Measurements of the Lateral Stability and Control Characteristics of a High-Speed Fighter Airplane

Flight Test of a Radial-Burning Solid-Fuel Ram Jet

Flight Measurements of the Effects of Surface Condition on the Supersonic Drag of Fin-Stabilized Parabolic Bodies of Revolution

Force Tests of Three Thin Wings of Moderately Low Aspect Ratio at High Subsonic Mach Numbers

Force and Pressure Investigation at Large Scale of a 49 Degree Sweptback Semispan Wing Having NACA 65A006 Sections and Equipped With Various Slat Arrangements

Investigation at Transonic Speeds of the Effect of a Positive-Lift Balancing Tab on the Hinge-Moment and Lift-Characteristics of a Full-Span Flap on a Tapered 45 Degrees Sweptback Wing of Aspect Ratio 3

An Investigation of a 0.16-Scale Model of the Douglas X-3 Airplane to Determine Means of Improving the Low-Speed Longitudinal Stability and Control Characteristics

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degrees Sweepback: Estimated Downwash Angles Derived From Pressure Measurements on the Tail at Mach Numbers of 1.40 and 1.59

Investigation at Mach Number 2.93 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control

Investigation at a Mach Number of 1.2 of Two 45 Degree Sweptback Wings Utilizing NACA 2-006 and NACA 65A006 Airfoil Sections

An Investigation at Transonic Speeds of the Aerodynamic Characteristics of an Air Inlet Installed in the Root of a 45 Degree Sweptback Wing

Investigation of a 10-Stage Subsonic Axial-Flow Research Compressor 2: Preliminary Analysis of Overall Performance

Preliminary Survey of Boundary-Layer Development at a Nominal Mach Number of 5.5

Calibration of AWS instrument shelter in Langley 300 MPH 7- by 10-foot tunnel

Development of Metal-Bonding Adhesive FPL-710 With Improved Heat-Resistant Properties

Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig

The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow

Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel

The Aerodynamic Design of High Mach Number Nozzles Utilizing Axisymmetric Flow with Application to a Nozzle of Square Test Section

Aerodynamic Characteristics of a Refined Deep-Step Planing-Tail Flying-Boat Hull with Various Forebody and Afterbody Shapes

Analogue-computer simulation of an autopilot servo system having nonlinear response characteristics

Achievement of Continuous Wall Curvature in Design of Two-Dimensional Symmetrical Supersonic Nozzles

The Aerodynamic Design of Supersonic Propellers from Structural Considerations

Aerodynamic Characteristics of Three Deep-Step Planing-Tail Flying-Boat Hulls and a Transverse-Step Hull with Extended Afterbody

Accuracy of Approximate Methods for Predicting Pressures on Pointed Nonlifting Bodies of Revolution in Supersonic Flow

Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Minimum Ignition of Six Pure Hydrocarbon Fuels of the C₂ and C₆ Series

Behavior of materials under conditions of thermal stress

NACA 65-series compressor rotor performance with varying annulus-area ratio, solidity, blade angle, and Reynolds number and comparison with cascade results

A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed

Some notes on the aerodynamic loads associated with external-store installations

Factors affecting transition at supersonic speeds

Two-dimensional low-speed cascade investigation of NACA compressor blade sections having a systematic variation in mean-line loading

Fuel characteristics pertinent to the design of aircraft fuel systems.Supplement 1 - Additional information on MIL-F-7914(AER) Grade JP-5 fuel and several fuel oils

Average skin-friction drag coefficients from tank tests of a parabolic body of revolution (NACA RM-10)

Effect of longitudinal wings position on the pressure characteristics at transonic speeds of a 45©� sweptback wing-fuselage model

Recent Results Pertaining to the Application of the "Area Rule"

Rocket-Model Investigation of the Longitudinal Stability, Drag, and Duct Performance Characteristics of the North American MX-770 (X-10) Missile at Mach Numbers from 0.80 to 1.70

Notes on the Prediction of Shock-induced Boundary-layer Separation

Flow Coefficients for Orifices in Base of Transpiration-Cooled Turbine Rotor Blade

Preliminary Transient Performance Data on the J73 Turbojet Engine, 3, Altitude, 45,000 Feet

Preliminary Transient Performance Data on the J73 Turbojet Engine. II - Altitude, 35,000 Feet

Theory of Wing-Body Drag at Supersonic Speeds

Rocket-model investigation of longitudinal stability and drag characteristics of an airplane configuration have a 60©� delta wing and a high unwept horizontal tail

Wind-tunnel investigation at high subsonic speeds of the effect of spoiler profile on the lateral control characteristics of a wing-fuselage combination winter quarter-chord line swept back 32.6©� and NACA 65A006 airfoil section


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