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Similar Solutions for the Compressible Laminar Boundary Layer with Heat Transfer and Pressure Gradient

Summary of results of a wind-tunnel investigation of nine related horizontal tails

A self-excited, alternating-current, constant-temperature hot-wire anemometer

Effects of sweep and angle of attack on boundary-layer transition on wings at Mach number 4.04

Preliminary Evaluation of Flight-Weight XRJ47-W-5 Ram-Jet Engine at a Mach Number of 2.75

Performance of a Single Fuel-Vaporizing Combustor With Six Injectors Adapted for Gaseous Hydrogen

Flight Characteristics of a Wingless Rocket- Powered Model With Four Externally Mounted Air-to-Air Missiles at Mach Numbers 0.7 to 1.6

Experimental Investigation at High Subsonic Speeds of the Rolling-Stability Derivatives of a 1/22 Scale Model of the Republic F-105 Airplane

Some Effects of Aeroelasticity on the Rolling Effectiveness of a 10-Percent-Scale Model of the Mcdonnell F-101A Airplane Wing at Mach Numbers From 0.5 to 1.2

Some Effects of Roll Rate on the Longitudinal Stability Characteristics of the Hughes Falcon Missile, ''C'' Configuration, for a Mach Number Range of 1.1 to 1.8 as Determined From Flight Test

Static Longitudinal and Lateral Stability and Control Characteristics of an 0.065-Scale Model of the Chance Vought Regulus 2 Missile at Mach Numbers of 1.41, 1.61, and 2.01 Research Memorandum

Preliminary Free-Jet Performance of XRJ43-MA-3 Ram-Jet Engine at a Mach Number of 2.70

Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds

Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets

Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder

Wind-Tunnel Measurements at Subsonic Speeds of the Static and Dynamic-Rotary Stability Derivatives of a Triangular-Wing Airplane Model Having a Triangular Vertical Tail

Effects of Various Modifications on the Static Longitudinal Stability and Control Characteristics of a 0.065-Scale Model of the Chance Vought Regulus II Missile at a Mach Number of 2.01

Effects of Free-Flight Rocket-Model Booster-Adapter Configurations on the Aerodynamic Characteristics in Pitch and Sideslip of a Swept-Wing Fighter Airplane Model at a Mach Number of 2.01

A Dye-Tracer Technique for Experimentally Obtaining Impingement Characteristics of Arbitrary Bodies and a Method for Determining Droplet Size Distribution

Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen

Liquid Hydrogen as a Jet Fuel for High-Altitude Aircraft

A Low-Pressure-Loss Short Afterburner for Sea-Level Thrust Augmentation

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder

Force and Pressure Measurements on Several Canopy-Fuselage Configurations at Mach Numbers 1.41 and 2.01

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 1. - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Lift and Drag; Mach Number, 1.61

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 3 - Swept-Wing Fighter-Bomber Configuration With Large and Small Stores. Mach Number, 1.61

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-fuselage-store Configurations 2 - Swept-wing Heavy-bomber Configuration With Large Store Nacelle. Lateral Forces and Pitching Moments, Mach Number, 1.61

The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 4. - Delta-Wing Heavy-Bomber Configuration With Large Store. Mach Number, 1.61

Analysis of Limitations Imposed on One-Spool Turbojet-Engine Designs by Turbines Having Downstream Stators at 0, 2.0, and 2.8 Flight Mach Numbers

Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Mach Numbers of 1.41, 1.61, and 2.01

An Investigation of Jet Effects on Adjacent Surfaces

Flight Investigation of a Roll-Stabilized Ramjet Test Vehicle Over a Mach Number Range of 2.3 to 2.7

Longitudinal Stability and Control Characteristics as Determined by the Rocket-Model Technique for an Inline, Cruciform, Canard Missile Configuration With a Low-Aspect-Ratio Wing Having Trailing-Edge Flap Controls for a Mach Number Range of 0.7 to 1.8

Low-Temperature Chemical Starting of a 200-Pound-Thrust JP-4 - Nitric Acid Rocket Engine Using a Three-Fluid Propellant Valve

An Investigation of the Longitudinal Stability Characteristics of Three Specialized Store Configurations at Transonic Speeds

Investigation of Porous Gas-Heated Leading-Edge Section for Icing Protection of a Delta Wing

NACA Conference on Aerodynamics of High Speed Aircraft

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Effects of Wing-Fuselage Flow Fields on Missile Loads at Subsonic Speeds

Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight

Investigation of a 1/4-Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Lateral Control and Directional Stability and Control Characteristics of Model Equipped With Drooped, Supersonic-Type, Elliptical Wing-Root Inlet

Investigation of a 1/4 Scale Model of the Republic F-105 Airplane in the Langley 19-Foot Pressure Tunnel: Longitudinal Stability and Control and Horizontal-Tail Hinge-Moment and Normal-Force Characteristics of the Model Equipped With a Drooped Supersonic-Type Elliptical Wing-Root Inlet

A Comparison of the Maneuvering Performance of a Monowing Versus a Cruciform Missile

Aerodynamic Characteristics of Two Rectangular-plan-form, Allmovable Controls in Combination With a Slender Body of Revolution at Mach Numbers From 3.00 to 6.25

Analysis of Low-Temperature Nuclear-Powered Ramjet Missile for High Altitudes

Chemical and Physical Properties of Modified Hi-Cal-2

Analysis of stresses in the plastic range around a circular hole in a plate subjected to uniaxial tension

Preliminary Investigation of a Submerged Air Scoop Utilizing Boundary-Layer Suction to Obtain Increased Pressure Recovery

A Preliminary Investigation of Aerodynamic Characteristics of Small Inclined Air Outlets at Transonic Mach Numbers


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