Browse TRAIL Inventories

Free-flight heat-transfer measurements on two 20 degree-cone-cylinders at Mach numbers from 1.3 to 4.9

Note on the Scavenge of 6-Inch-Diameter Ram-Jet Exhaust in Mach 3.1, 1- by 1-Foot Supersonic Tunnel

Performance of a double-cone inlet with and without a shroud at below-design Mach numbers

Effect of flight speed on dynamics of a turboprop engine

Correlation of turbine-blade-element losses based on wake momentum thickness with diffusion parameter for a series of subsonic turbine blades in two-dimensional cascade and for four transonic turbine rotors

An experimental evaluation of several design variations of hollow turbine blades for expendable engine application

Drag and rolling-moment effectiveness of trailing-edge spoilers at Mach numbers 2.2 and 5.0

Drag near zero lift of a 1/7-scale model of the Convair B-58 external store as measured in free flight between Mach numbers of 0.8 and 2.45

Design and test of mixed-flow impellers 6: performance and parabolic-bladed impeller with shroud redesigned by rapid approximate method

Design and test of mixed-flow impellers 5: design procedure and performance results for two vaned diffusers tested with impeller model MFI-1B

Design considerations of a condensing system for vaporized magnesium

A study of service-imposed maneuvers of four jet fighter airplanes in relation to their handling qualities and calculated dynamic characteristics

Analytical evaluation of effect of inlet-air temperature and combustion pressure on combustion performance of boron slurries and blends of pentaborane

Comparison between analytical and wind-tunnel results on flutter of several low-aspect-ratio, high-density, unswept wings at high subsonic speeds and zero angle of attack

Aerodynamic characteristics of various configurations of a model of a 45 degree swept-wing airplane at a Mach number of 2.01

Analysis of a pressure-jet power plant for helicopter

Analysis of effects of airplane characteristics and autopilot parameters on a roll-command system with aileron rate and deflection limiting

Boundary-layer transition at high Reynolds numbers as obtained in flight of a 20 degree cone-cylinder with wall to local stream temperature ratios near 1.0

Effects of increasing Reynolds number from 2 x 10(exp 6) to 6 x 10(exp 6) on the aerodynamic characteristics at transonic speeds of a 45 degree swept wing with 6 degree leading-edge droop

Effects of inlet-flow-air distortion on steady-state altitude performance of an axial-flow turbojet engine

Effectiveness of a turbojet tubular combustor in screening the turbine from foreign objects

Effect of fuel nozzle protrusion on transient and steady-state turbojet combustor performance

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 : TED No. NACA AD 398

Effects of turbine cooling with compressor air bleed on gas-turbine engine performance

The effects of trailing-edge flaps on the subsonic aerodynamic characteristics of an airplane model having a triangular wing of aspect ratio 3

Experimental investigation of methods of improving diffuser-exit total-pressure profiles for side-inlet model at Mach number 3.05

Estimation of Incremental Pitching Moments Due to Trailing-Edge Flaps on Swept and Triangular Wings

Experimental determination of the aerodynamic derivatives arising from acceleration in sideslip for a triangular, a swept, and an unswept wing

Experimental investigation of some aerodynamic effects of a gap between wing and body of a moderately slender wing-body combination at a Mach number of 1.4

An experimental investigation of the air-flow of a scoop-type normal-shock inlet

Aerodynamic characteristics of a 60 degree delta wing having a half-delta tip control at a Mach number of 4.04

Effect of compression-inlet area blockage on performance of an experimental compressor and a hypothetical noise

Experimental studies of flutter of buckled rectangular panels at Mach numbers from 1.2 to 3.0 including effects of pressure differential and of panel width-length ratio

The effect of control stiffness and forward speed on the flutter of a 1/10-scale dynamic model of a two-blade jet-driven helicopter rotor

Aluminum borohydride - hydrocarbon mixtures as a source of ignition for a turbojet combustor

A systematic study of the effects of leading-edge chord-extensions on the low-speed longitudinal stability characteristics of three 45 degree sweptback wings

Some studies of axisymmetric free jets exhausting from sonic and supersonic nozzles into still air and into supersonic streams

Steady-state and surge characteristics of a compressor equipped with variable inlet guide vanes operating in a turbojet engine

Statistical measurements of landing-contact conditions of a heavy bomber

Summary of the flight conditions and maneuvers in which maximum wing and tail loads were experienced on a swept-wing fighter airplane

Simplified procedures for estimating flap-control loads at supersonic speeds

A study of flame-holder elements for use in high-velocity afterburners

Statistical measurements of landing contact conditions of the Boeing B-47 airplane

Simulator studies of a simple homing system

Static longitudinal and lateral stability and control characteristics of a model of a 35 degree swept-wing airplane at a Mach number of 1.41

Static longitudinal and lateral stability and control characteristics of an 0.065-scale model of the Chance Vought Regulus II missile at Mach numbers of 1.41, 1.61, and 2.01 : TED No. NACA AD 398

Static longitudinal and lateral stability and control data from an exploratory investigation at a Mach number of 6.86 of an airplane configuration having a wing of trapezoidal plan form

Static longitudinal and lateral stability data from an exploratory investigation at Mach number 4.06 of an airplane configuration having a wing of trapezoidal plan form

Static longitudinal and lateral stability and control characteristics of an airplane configuration having a wing of trapezoidal plan form with various tail airfoil sections and tail arrangements at a Mach number of 6.86

Removal of secondary-flow accumulations in a two-dimensional turbine nozzle passage by boundary-layer bleed


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