Browse TRAIL Inventories

Choking of a Subsonic Induction Tunnel by the Flow from an Induction Nozzle

Equivalent-Plate Theory for a Straight Multicell Wing

On the Application of Transonic Similarity Rules

An Analysis of Laminar Free-Convection Flow and Heat Transfer About a Flat Plate Parallel to the Direction of the Generating Body Force

Introduction to Electrical-Circuit Analogies for Beam Analysis

A Simple Numerical Method for the Calculation of the Laminar Boundary Layer

Transition Caused by the Laminar Flow Separation

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

An Investigation of Longitudinal Control Characteristics of a Wing-Tip Control Surface on a Sweptback Wing at Transonic Speeds by the NACA Wing-Flow Method

Investigation of Drag and Pressure Recovery of a Scoop Inlet in the Transonic Speed Range

Investigation of an NACA 4-(5)(05)-041 Four-Blade Propeller With Several Spinners at Mach Numbers Up to 0.90

Flight Investigation From Mach Number 0.8 to 2.0 to Determine Some Effects of Wing-to-Tail Distance on the Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Canard Missile

Flight Measurements at Mach Numbers From 1.1 to 1.9 of the Zero-Lift Drag of a Twin-Engine Supersonic Ram-Jet Configuration

Handling Qualities of High-Speed Airplanes

Hydrodynamic Directional Behavior of a Swept Planing-Tail Hull

An Investigation of the Stream-Tube Power Losses and an Improvement of the Diffuser-Entrance Nose in the Langley 8-Foot Transonic Tunnel

Investigation of Turbines for Driving Supersonic Compressors 2: Performance of First Configuration With 2.2 Percent Reduction in Nozzle Flow Area

Longitudinal Frequency-Response Characteristics of the Douglas D-558-I Airplane as Determined From Experimental Transient-Response Histories to Mach Number of 0.90

Longitudinal Frequency-Response and Stability Characteristics of the Douglas D-558-II Airplane as Determined From Transient Response to a Mach Number of 0.96

The Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing Missile Having Half-Delta Tip Controls as Obtained From a Free-Flight Investigation at Transonic and Supersonic Speeds

Longitudinal Stability and Control Characteristics of a Canard Missile Configuration for Mach Numbers From 1.1 to 1.93 as Determined From Free-Flight and Wind-Tunnel Investigation

Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.70 to 1.37 of Rocket-Propelled Models Having a Modified Triangular Wing

Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.75 to 1.5 of an Airplane Configuration Having a 60 Degree Swept Wing of Aspect Ratio 2.24 as Obtained From Rocket-Propelled Models

A Low-Speed Experimental Study of the Directional Characteristics of a Sharp-Nosed Fuselage Through a Large Angle-of-Attack Range at Zero Angle of Sideslip

Low-Speed Wind-Tunnel Investigation of the Effects of Propeller Operation at High Thrust on the Longitudinal Stability and Trim of a Twin-Engine Airplane Configuration

Investigation of the Effects of Variations in the Reynolds Number Between 0.4 X 10(Exp 6) 3.0 X 10(Exp 6) on the Low-Speed Aerodynamic Characteristics of Three Low-Aspect-Ratio Symmetrical Wings With Rectangular Plan Forms

An Investigation of Propeller Vibrations Excited by Wing Wakes

Investigation of the Distribution of Lift, Drag, and Pitching Moment Between the Wing and Fuselage of a 1/30-Scale Semispan Model of the Bell X-5 Airplane at a Mach Number of 1.24 by the NACA Wing-Flow Method

Investigation of Turbines for Driving Supersonic Compressors: 1: Design and Performance of First Configuration

Investigation of Titanium Carbide Base Ceramals Containing Either Nickel or Cobalt for Use as Gas-Turbine Blades

An Investigation of the Low-Speed Longitudinal Stability Characteristics of a Swept-Wing Airplane Model With Two Modifications to the Wing-Root Plan Form

Investigation of the Low-Speed Aerodynamic Characteristics of a Variable-Sweep Airplane Model With a Twisted and Cambered Wing

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


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