Browse TRAIL Inventories

A method of measuring jet thrust of turbojet engines in flight installations

Effect of horizontal-tail span and vertical location on the aerodynamic characteristics of an unswept tail assembly in sideslip

Formation and combustion of smoke in laminar flames

Convection of a pattern of vorticity through a shock wave

Low-Speed Longitudinal Stability and Lateral-Control Characteristics of a 0.3-Scale Model of the Republic RF-84F Airplane at a Reynolds Number of 9x10(exp 6)

Effect of ground interference on the aerodynamic and flow characteristics of a 42 degree sweptback wing at Reynolds numbers up to 6.8 x 10(6)

Exact solutions of laminar-boundary-layer equations with constant property values for porous wall with variable temperature

A study of the characteristics of human-pilot control response to simulated aircraft lateral motions

Structural response to discrete and continuous gusts of an airplane having wing bending flexibility and a correlation of calculated and flight results

A visualization study of secondary flows in cascades

Experimental investigation of acceleration characteristics of a turbojet engine including regions of surge and stall for control applications

Comparison of performance of experimental and conventional cage designs and materials for 75-millimeter-bore cylindrical roller bearings at high speed

Effects of sweep and thickness on the static longitudinal aerodynamic characteristics of a series of thin, low-aspect-ratio, highly tapered wings at transonic speeds: transonic-bump method

Wind-tunnel investigation at low speed of the effects of chordwise wing fences and horizontal-tail position on the static longitudinal stability characteristics of an airplane model with a 35 degree sweptback wing

Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Fighter Model Employing a Low-aspect-ratio Unswept Wing and a Horizontal Tail Mounted Well above the Wing Plane - Lateral and Directional Stability

Effect of a Leading-edge Flap upon the Lift, Drag, and Pitching Moment of an Airplane Employing a Thin, Unswept Wing

Longitudinal Stability Characteristics of the Consolidated Vultee XFY-1 Airplane with Windmilling Propellers as Obtained from Flight of 0.133-Scale Rocket-Propelled Model at Mach Numbers from 0.70 to 1.13

Analysis of Rocket, Ram-Jet, and Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2 - Rocket Missile Performance

Note on the Effects of First-Order Aerodynamic Loads on Propeller Shaft Loads with Emphasis on Counterrotating Propellers

Preliminary Investigation of the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds

High-Speed Drag and Opening Characteristics of a Kaman Rotochute Model

Vapor pressures and calculated heats of vaporization of concentrated nitric acid solutions in the composition range 71 to 89 percent nitrogen dioxide, 1 to 10 percent water, and in the temperature range 10 to 60 degrees C

A flight evaluation of the stability and control of the X-4 swept-wing semitailless airplane

Flight determination of the drag of conical-shock nose inlets with various cowling shapes and axial positions of the center body at Mach numbers from 0.8 to 2.0

Exploratory engine test of transpiration-cooled turbine-rotor blade with wire-cloth shell

High-altitude performance of an experimental turbular prevaporizing combustor

Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction I : performance of rotor alone

Investigation of a trailing-edge paddle-control surface on a triangular wing of aspect ratio 2 at subsonic and supersonic speeds

Investigation of a supersonic-compressor rotor with turning to axial direction II : rotor component off-design and stage performance

Investigation of a translating-cone inlet at Mach numbers from 1.5 to 2.0

Internal performance at Mach number to 2.0 of two auxiliary inlets immersed in fuselage boundary layer

Investigation of a high-temperature single-stage turbine suitable for air cooling and turbine stator adjustment 1: design of vortex turbine and performance with stator at design setting

Investigation of a high-temperature single-stage turbine suitable for air cooling and turbine stator adjustment 2: performance of vortex turbine at various stator settings

Investigation of a high-pressure ratio eight-stage axial-flow research compressor with two transonic inlet stages III : individual stage performance characteristics

Investigation of a missile airframe with control surfaces consisting of projecting quadrants of the nose cone

Investigation of a 10-stage subsonic axial-flow research compressor V : effect of reducing inlet-guide-vane turning on over-all and inlet-stage performance

Investigation of a 10-stage subsonic axial-flow research compressor VI : performance evaluation and flow distributions in the first, fifth, and tenth stages

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback : aerodynamic characteristics of the configuration equipped with a canard control surface at a Mach number of 1.89

Investigation of Supersonic-Compressor Rotors Designed with External Compression

Investigation of three highly loaded subsonic-inlet-stage axial-flow compressors employing varying radial gradients of energy addition

Investigation of three low-temperature-ratio combustor configurations in a 48-inch-diameter ram-jet engine

Investigation of transient combustion characteristics in a single tubular combustor

Investigation to Mach number 2.0 of shock-positioning control systems for a variable-geometry inlet in combination with a J34 turbojet engine

A method for increasing the effectiveness of stabilizing surfaces at high supersonic Mach numbers

Method for studying helicopter longitudinal maneuver stability

Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds

Pressure distributions on triangular and rectangular wings to high angles of attack Mach numbers 1.45 and 1.97

Performance of isentropic nose inlets at Mach number of 5.6

Performance of two air-cooled turbojet engines determined analytically from engine component performance for a range of cooling-air weight flows

Performance of wedge-type boundary layer diverters for side inlets at supersonic speeds


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