Browse TRAIL Inventories

Effect of spark repetition rate on the ignition limits of a single tubular combustor

Heat capacity lag in gases

Notes on low-lift buffeting and wing dropping at Mach numbers near 1

Determination of ram-jet combustion-chamber temperatures by means of total-pressure surveys

Criterions for prediction and control of ram-jet flow pulsations

The effect of mass distribution on the low-speed dynamic lateral stability and control characteristics of a model with a 60 degree triangular wing

An analytical investigation using aerodynamic limitations of several designs of high stage pressure ratio multistage compressors

Analytical investigation of ram-jet-engine performance in flight Mach number range from 3 to 7

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc section and 40 degree sweepback: a pressure-distribution study of the aerodynamic characteristics of the wing at Mach number 1.40

Aerodynamic characteristics of wings designed for structural improvement

Calculated effects of turbine rotor-blade cooling-air flow, altitude, and compressor bleed point on performance of a turbojet engine

Ceramic coatings for prevention of carbon absorption in four heat-resistant alloys

Combustion performance evaluation of magnesium-hydrocarbon slurry blends in a simulated tail-pipe burner

Combustion properties of aluminum as ram-jet fuel

Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected

Apparatus for obtaining a supersonic flow of very short duration and some drag measurements obtained with its use

Analysis of longitudinal stability and trim of the Bell X-1 airplane at a lift coefficient of 0.3 to Mach numbers near 1.05

Low-speed longitudinal and wake air-flow characteristics at a Reynolds number of 5.5 x 10(exp 6) of a circular-arc 52 degrees sweptback wing with a fuselage and a horizontal tail at various vertical positions

Characteristics of flow over inclined bodies of revolution

Compressor performance characteristics of a python turbine-propeller engine investigated in altitude wind tunnel

Analysis of experimental sea-level transient data and analog method of obtaining altitude response for turbine-propeller engine with relay-type speed control

The effects of Mach number and Reynolds number on the aerodynamic characteristics of several 12-percent-thick wings having 35 degrees of sweepback and various amounts of camber

Effects of humidity during fabrication on some physical properties of glass-fabric unsaturated-polyester laminates

Evaluation of centrifugal compressor performance with water injection

The effects of various parameters including Mach number on propeller blade flutter with emphasis on stall flutter

Experimental investigation of oil film pressure distribution for misaligned plain bearings

Estimated deceleration of airplane nose section jettisoned at various altitudes and airspeeds

Experimental and theoretical study of the effects of body size on the aerodynamic characteristics of an aspect ratio 3.0 wing-body combination

Experimental investigation of effects of design changes on performance of large-capacity centrifugal compressors

Aerodynamic characteristics at transonic speeds of a 69 degree delta wing with a triangular plan-form control having a skewed hinge axis and an overhang balance : transonic-bump method

Aerodynamic characteristics including pressure distribution of a fuselage and three combinations of the fuselage with swept-back wings at high subsonic speeds

Ignition-energy requirements in a single tubular combustor

Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated stall and in pull-ups at Mach numbers of 0.74, 0.75, 0.94, and 0.97

Tabulated pressure coefficients and aerodynamic characteristics measured on the wing of the Bell X-1 airplane in an unaccelerated low-speed stall, in push-overs at Mach numbers of 0.83 and 0.99, and in a pull-up at a Mach number of 1.16

Simplified method for calculation of compressible laminar boundary with arbitrary free-stream pressure gradient

Some properties of beryllium oxide and beryllium oxide - columbium ceramals

Some low-speed characteristics of an air-induction system having scoop-type inlets with provisions for boundary-layer control

Status of combustion research on high-energy fuels for ram jets

Sound from a two-blade propeller at supersonic tip speeds

Static longitudinal stability and dynamic characteristics at high angles of attack and at low Reynolds numbers of a model of the X-3 supersonic research airplane

The properties of three cast polyester resins of Sierracin 212, 212A, and 250A

A study of slip formation in polycrystalline aluminum

An experimental study at moderate and high subsonic speeds of the flow over wings with 30 degrees and 45 degrees of sweepforward in conjunction with a fuselage

Dynamic stability and control characteristics of a vertically rising airplane model in hovering flight

An experimental study at moderate and high subsonic speeds of the flow over wings with 30 degrees and 45 degrees of sweepback in conjunction with a fuselage

Investigation in the Ames 12-foot pressure wind tunnel of a model horizontal tail of aspect ratio 3 and taper ratio 0.5 having the quarter-chord line swept back 45 degrees

Investigation of altitude starting and acceleration characteristics of J47 turbojet engine

Subsonic Mach and Reynolds number effects on the surface pressures, gap flow, pressure recovery, and drag of a nonrotating NACA 1-series E-type cowling at an angle of attack of 0 degrees

A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2 : wing-fuselage configuration having a wing of 60 degree sweepback, aspect-ratio 4, taper ratio 0.6, and NACA 65A006 airf

A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2. : wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai


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