TRAIL - Technical Report Archive and Image Library

Wind-Tunnel Investigation at High Subsonic Speeds of the Effects on Static Stability Characteristics of Various Modifications to a Swept-Wing Fighter-Type Airplane Model

A Wind-Tunnel Investigation of the Effects of Conical Camber for an Airplane Configuration Having a Triangular Wing of Aspect Ratio 2.2

Wind-Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-Wing Airplane With Blowing Flaps and Leading-Edge Slats

Aerodynamics of Oscillating Control Surfaces at Transonic Speeds

Material Compatibility With Gaseous Fluorine

Measurement of Static Forces on Internally Carried Bombs of Three Fineness Ratios in Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.61 With Illustrative Drop Path Calculations

Flight Investigation of Pentaborane Fuel in 9.75-inch-diameter Ram-jet Engine With Downstream Fuel Injection

High-Altitude Performance of J71-A-11 Turbojet Engine and Its Components Using JP-4 and Gaseous-Hydrogen Fuels

Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Mach Number 1.59

Investigation of the Low-Speed Flight Characteristics of a 1/15-Scale Model of the Convair XB-58 Airplane

Wind-Tunnel Tests of a Series of Practice Bombs

Transonic Flutter Investigation of an All-Movable Horizontal Tail for a Fighter Airplane

Dynamic Stability Investigation of Two Right Circular Cylinders in Axial Free Flight at Mach Numbers From 0.4 to 1.7 Fineness-Ratio- 2.56 Cylinder and Fineness-Ratio-4.0 Cylinder With Flared Afterbody

Experimental Performance of a 5000-Pound-Thrust Rocket Chamber Using a 20-Percent-Fluorine - 80-Percent-Oxygen Mixture With RP-1

Experimental Investigation of the Transonic and Supersonic Flutter Characteristics of the Upper and Lower Vertical Tails of an Air-to-Ground Missile

Effect of Hinge-Line Position on the Oscillating Hinge Moments and Flutter Characteristics of a Flap-Type Control at Transonic Speeds

Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 2 - Design and Experimental Performance of Turbine With Low-Velocity-Turning Stator and Standard Rotor

Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 3 - Experimental Performance With Two Stator Configurations Designed to Eliminate Blade Wakes and Secondary-Flow Effects and Conclusions From Entire Stator Investigation

Investigation of an Afterburning Ramjet Using Gaseous Hydrogen as Fuel at Mach Number of 3.0

Investigation of an Air-Cooled, Plug-Type, Variable-Area Exhaust Nozzle

Investigation of an Underslung Normal-Wedge Inlet at Free-Stream Mach Numbers From 1.50 to 1.99

Investigation of an Underslung Scoop Inlet at Mach Numbers to 1.99

Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06

Investigation of Ejection Releases of an MB-1 Rocket From a 0.04956-Scaled Model of the Convair F-106A Airplane at Several Mach Numbers and Simulated Altitudes

Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine

Heat Transfer in Regions of Separated and Reattached Flows

In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System

Investigation of High-Angle-of-Attack Performance of a 14 Deg Ramp-Type Inlet in Various Circumferential Body Locations: Mach Number Range 1.5 to 2.0

Investigation of Static Pressures and Boundary-Layer Characteristics on the Forward Parts of Nine Fuselages of Various Cross-Sectional Shapes at M Infinity Equal 2.01

Analysis of Fluorine Addition to the Vanguard First Stage

Brief Studies of Turbojet Combustor and Fuel-System Operation With Hydrogen Fuel at -400 Degrees F

Aerodynamic Forces and Moments on a Large Ogive-Cylinder Store at Various Locations Below the Fuselage Center Line of a Swept-Wing Bomber Configuration at a Mach Number of 1.61

Simplified Theory for Dynamic Relation of Ramjet Pressures and Fuel Flow

Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations

Thermal Stability of a Commercial Propyl Pentaborane (HEF-2) in the Range 147 Degree to 190 Degree C

A Summary of the Longitudinal and Lateral Stability and Control Characteristics Obtained From Rocket-Model Tests of a Swept-Wing Fighter-Type Airplane at Mach Numbers From 0.5 to 1.9

Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2

Tabulated Pressure Data for a Series of Controls on a 40 Degree Sweptback Wing at Mach Numbers of 1.61 and 2.01

Total-Pressure Distortion and Recovery of Supersonic Nose Inlet With Conical Centerbody in Subsonic Icing Conditions

Preliminary Investigation of Dynamic Lateral Stability Characteristics of a Configuration of the North American X-15 Research Airplane

Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane

Heat-Transfer and Pressure Measurements from a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 by 10 to the 6th Power

Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration

Flutter Experiments With Various Control Configurations

Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control

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