Browse TRAIL Inventories

Boundary-layer measurements in 3.84- by 10-inch supersonic channel

Theoretical turbojet thrust augmentation by evaporation of water during compression as determined by use of a Mollier diagram

Method for determining optimum division of power between jet and propeller for maximum thrust power of a turbine-propeller engine

A survey of the flow at the plane of the propeller of a twin-engine airplane

Investigation of flap-type ailerons on an untapered wing having an aspect ratio of 3.7, 45 degree sweepback, and an NACA 65A009 airfoil section : transonic-bump method

Flight determination of the effects of rudder-pedal-force characteristics on the aiming error in azimuth of a conventional fighter airplane

Initial flight investigation of a twin engine supersonic ram jet

Fundamental flame velocities of pure hydrocarbons 2: alkadienes

Fundamental flame velocities of pure hydrocarbons 1: alkanes, alkenes, alkynes benzene, and cyclohexane

High-speed aerodynamic characteristics of a lateral-control model 3: section characteristics, fence studies, and tabulated pressure coefficients with modified NACA 0012-64 section, 26.6-percent-chord, plain aileron, 0 and 45 degree sweepback

Investigation of perforated convergent-divergent diffusers with initial boundary layer

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback: Static longitudinal stability and control characteristics at a Mach number of 1.59

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.59

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : static lateral stability characteristics at Mach numbers of 1.40 and 1.59

Investigation of a 1/5-scale model of a proposed high-submerged-speed submarine in the Langley full-scale tunnel

Investigation of ignition characteristics of AN-F-32 and two AN-F-58a fuels in single can-type turbojet combustor

The transonic characteristics of a low-aspect-ratio triangular wing with a constant-chord flap as determined by wing-flow tests, including correlation with large-scale tests

Tests of a small-scale NACA submerged inlet at transonic Mach numbers

Influence of tube-entrance configuration on average heat-transfer coefficients and friction factors for air flowing in an Inconel tube

Investigation of stage performance of X24C-2 ten-stage axial-flow compressor at design speed

Preliminary flight investigation of the wing-dropping tendency and lateral-control characteristics of a 35 degree swept-wing airplane at transonic Mach numbers

Measurements of the effect of trailing-edge thickness on the zero-lift drag of thin low-aspect-ratio wings

Effects of sweep on the damping-in-roll characteristics of three sweptback wings having an aspect ratio of 4 at transonic speeds

An NACA transonic test section with tapered slots tested at Mach numbers to 1.26

Performance of high-pressure-ratio axial-flow compressor using highly cambered NACA 65-series blower blades at high Mach numbers

NACA research on combustors for aircraft gas turbines I : effects of operating variables on steady-state performance

Large-scale flight measurements of zero-lift drag at Mach numbers form 0.86 to 1.5 of a wing-body combination having a 60 degree triangular wing with NACA 65A003 sections

Preliminary correlation of efficiency of aircraft gas-turbine combustors for different operating conditions

Preliminary analysis of effects of air cooling turbine blades on turbojet-engine performance

Preliminary investigation of constant-geometry, variable Mach number, supersonic tunnel with porous walls

Preliminary flight investigation of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane

Preliminary analysis of three cycles for nuclear propulsion of aircraft

Lift and moment characteristics at subsonic Mach numbers of four 10-percent-thick airfoil sections of varying trailing-edge thickness

Lateral-control investigation of flap-type and spoiler-type controls on a wing with quarter-chord-line sweepback of 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Lateral-control investigation of flap-type controls on a wing with upswept quarter-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method

Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method

Longitudinal-stability characteristics of the Northrop X-4 airplane (USAF No. 46-677)

Low-speed investigation of leading-edge and trailing-edge flaps on a 47.5 degree sweptback wing of aspect ratio 3.4 at a Reynolds number of 4.4 x 10(exp 6)

Measurement of uniform flame movement in carbon monoxide - air mixtures containing either added D2O or H2O

Measurements of the drag and pressure distribution on a body of revolution throughout transition from subsonic to supersonic speeds

Temperature survey of the wake of two closely located parallel jets

Free-spinning tunnel tests of a 1/20-scale model of the McDonnell XF3H-1 airplane : TED No. NACA DE 343

Free-jet investigation of a 16-inch ram jet at Mach numbers of 1.35, 1.50, and 1.73

Free-jet performance of 16-inch ram-jet engine with several fuels

Heat-transfer and operating characteristics of aluminum forced-convection and stainless-steel natural-convection water-cooled single-stage turbines

Note on some observed effects of rocket motor operation on the base pressures of bodies in free light

Free-flight performance of 16-inch-diameter supersonic ram-jet units 2: five units designed for combustion-chamber-inlet Mach number of 0.16 at free-stream Mach number of 1.60 (units B-1, B-2, B-3, B-4, and B-5)

Flight measurements with the Douglas D-558-II (BuAero No. 37974) research airplane : determination of the aerodynamic center and zero-lift pitching-moment coefficient of the wing-fuselage combination by means of tail-load measurements in the Mach num

Effect of fuel volatility on altitude starting limits of a turbojet engine


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