TRAIL - Technical Report Archive and Image Library

A comparison of two methods for calculating transient temperatures for thick walls

Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01

Investigation of Reynolds number effect on performance of an eight-stage axial-flow research compressor with long- and medium-chord lengths in the two transonic inlet stages

Preliminary analysis of over-all performance of an eight-stage axial -flow research compressor with two long-chord transonic inlet stages

Tabulated pressure data for a 60 degree delta-wing-body-tail model with a hot jet exhausting from a pylon-mounted nacelle

Supersonic wave interference affecting stability

Propellant vaporization as a criterion for rocket engine design : relation between percentage of propellant vaporized and engine performance

Similar solutions for the compressible boundary layer on a yawed cylinder with transpiration cooling

Some factors affecting the variation of pitching moment with sideslip of aircraft configurations

Study of exit phase of flight of a very high altitude hypersonic airplane by means of a pilot-controlled analog computer

The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane

Results of an experimental investigation of small viscous dampers

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: lateral-directional characteristics of a triangular wing and canard

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: triangular wing and canard on an extended body

Static stability and control characteristics of a triangular wing and canard configuration at Mach numbers form 2.58 to 3.53

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22: longitudinal characteristics of an unswept wing and canard

The static longitudinal characteristics of a twisted and cambered 45 degree sweptback wing at Mach numbers up to 0.96

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22 : longitudinal characteristics of a triangular wing and canard

Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22longitudinal characteristics of a triangular wing and unswept canard

Propellant vaporization as a criterion for rocket-engine design : calculations of chamber length to vaporize various propellants

Survey of supersonic inlets for high Mach number applications

Effects of vertical location of the wing and horizontal tail on the static lateral and directional stability of a trapezoidal-wing airplane model at Mach numbers of 1.41 and 2.01

Experimental measurements of the effects of airplane motions on wing and tail angles of attack of a swept-wing bomber in rough air

Experimental results of an investigation of two methods of inflight thrust measurement applicable to afterburning turbojet engines with ejectors

An experimental investigation of wake effects on hydro-skis

Effect of a stringer on the stress concentration due to a crack in a thin sheet

Effect of a hot-jet exhaust on pressure distributions and external drag of several afterbodies on a single-engine airplane model at transonic speeds

Dynamic stability of vehicles traversing ascending or descending paths through the atmosphere

Effect of aerodynamic heating on the flutter of a rectangular wing at a Mach number of 2

Effects of nose angle and Mach number on transition on cones at supersonic speeds

Effects of frequency and amplitude on the yawing derivatives of triangular, swept, and unswept wings and of a triangular-wing-fuselage combination with and without a triangular tail performing sinusoidal yawing oscillations

Effects of fixing transition on the transonic aerodynamic characteristics of a wing-body configuration at Reynolds numbers from 2.4 to 12 million

Idealized wings and wing-bodies at a Mach number of 3

Flight investigation of the acceptability of a small side-located controller used with an irreversible hydraulic control system

General solutions for flow past slender cambered wings with swept trailing edges and calculation of additional loading due to control surfaces

Free-flight pressure measurements over a flare-stabilized rocket model with a modified Von Karman nose for Mach numbers up to 4.3

Transonic drag of several jet-noise suppressors

Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 4: rotor loss patterns as determined by hot-wire anemometers with rotor operating in a circumferentially uniform inlet flow field

Incipient spin characteristics of a 1/25-scale model of the Chance Vought XF8U-1 airplane: TED No. NACA AD 3118

Induction system characteristics and engine surge occurrence for two fighter-type airplanes

Subsonic aerodynamic characteristics up to extreme angles of attack of an airplane model having an unswept wing and a high horizontal tail

Summary of experimental heat-transfer measurements in turbulent flow for a Mach number range from 0.87 to 5.05

Summary of locations, extents, and intensities of turbulent areas encountered during flight investigations of the jet stream from January 7, 1957 to April 28, 1957

Theoretical combustion performance of several high-energy fuels for ramjet engines

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

A wind-tunnel investigation of several wingless missile configurations at supersonic speeds

Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane

Tests of ring-stiffened circular cylinders subjected to a transverse shear load

The adhesion of molten boron oxide to various materials

Aerodynamic characteristics at Mach numbers 2.36 and 2.87 of an airplane configuration having a cambered arrow wing with a 75 degree swept leading edge

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