Browse TRAIL Inventories

Flight determination of the longitudinal stability of a 1/10-scale rocket-powered model of the Northrop MX-775A missile at low lift coefficients and Mach numbers from 0.89 to 1.34

Effects of the spanwise, chordwise and vertical location of an external store on the aerodynamic characteristics of a 60 degree delta wing at Mach numbers of 1.41, 1.62, and 1.96

Control characteristics of trailing-edge spoilers on untapered blunt trailing-edge wings of aspect ratio 2.7 with 0 degree and 45 degrees sweepback at Mach numbers of 1.41 and 1.96

Effects of systematically varying the spanwise and vertical location of an external store on the aerodynamic characteristics of an unswept tapered wing of aspect ratio 4 at Mach numbers of 1.41, 1.62, and 1.96

Full-scale wind-tunnel investigation of the effects of wing modifications and horizontal-tail location on the low-speed static longitudinal characteristics of a 35 degree swept-wing airplane

Investigation of lift and center of pressure of low-aspect-ratio, cruciform, triangular, and rectangular wings in combination with a slender fuselage at high supersonic speeds

Investigation of performance of several double-shroud ejectors and effect of variable-area exhaust nozzle on single ejector performance

Investigation of power extraction characteristics and braking requirements of a windmilling turbojet engine

Investigation of losses in the XJ35-A-23 two-stage turbine

Investigation of internal film cooling of exhaust nozzle of a 1000-pound-thrust liquid-ammonia liquid-oxygen rocket

Investigation of a 10-stage subsonic axial-flow research compressor I : aerodynamic design

Investigation of heat-transfer coefficients in an afterburner

Wing load distribution on a swept wing airplane in flight at Mach numbers up to 1.11, and comparison with theory

Variation of pressure limits of flame propagation with tube diameter for various isooctane-oxygen-nitrogen mixtures

Comparison between prediction and experiment for all-movable wing and body combinations at supersonic speeds - drag due to lift and lift-drag ratio

Instrumentation and calibration technique for flight calibration of angle-of-attack systems on aircraft

Instrumentation of the Ames supersonic free-flight wind tunnel

Investigation of thrust augmentation using water-alcohol injection on a 5200-pound-thrust axial-flow-type turbojet engine at static sea-level conditions

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor tip-speed II : velocity-diagram study of turbine for engine operation with constant exhaust-nozzle area

Investigation of stresses due to thermal gradients in typical aircraft structures

Investigation of vanes immersed in the jet of a solid-fuel rocket motor

Investigations of air-cooled turbine rotors for turbojet engines 2: mechanical design, stress analysis, and burst test of modified J33 split-disk rotor

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed III : velocity-diagram study of two-stage and downstream-stator turbines for engine operation at constant rotative speed

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed I : turbine-design requirements for several engine operating conditions

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed IV : effect of increasing blade speed on velocity diagrams of turbine for engine operation at constant rotative speed

Investigation of ram-jet afterburning as a means of varying effective exhaust nozzle area

Investigation of several techniques for improving altitude starting limits of turbojet engines

An investigation of several supersonic missile configurations directed toward minimizing center-of-pressure travel

Measurements of pressure drop with no heat addition on mockup segments of the general electric air-cooled aircraft reactor

Preliminary investigation at transonic speeds of the effect of balancing tabs on the hinge-moment and other aerodynamic characteristics of a full-span flap on a tapered 45 degree sweptback wing of aspect ratio 3

Procedure for calculating turbine blade temperatures and comparison of calculated with observed values for two stationary air-cooled blades

Comparison between prediction and experiment for all-movable wing and body combinations at supersonic speeds: Lift, pitching moment, and hinge moment

Effects of internal corner fillets on pressure recovery: Mass flow characteristics of scoop-type conical supersonic inlets

Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 1: two-dimensional compression-ramp inlets with semicircular cowls

Effect of radiant energy on vaporization and combustion of liquid fuels

Performance of an impulse-type supersonic compressor with stators

Performance of the components of the XJ34-WE-32 turbojet engine over a range of engine and flight conditions

Performance of pure fuels in a single J33 combustor I : five liquid hydrocarbon fuels

Over-all performance of the J71 three-stage turbine

Performance of air inlets at transonic and low supersonic speeds

Oxidation-resistance mechanism and other properties of molybdenum disilicide

Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics

Normal accelerations and associated operating conditions on four types of commercial transport airplanes from VGH data available as of September 1951

Investigation of afterburner performance and afterburner fuel system coking of the Westinghouse XJ34-WE-32 engine

Preliminary investigation of a chemical starting technique for the acid - gasoline rocket propellant system

Preliminary investigation of corrosion by molten sodium hydroxide flowing in tubes of AISI 347 stainless steel, Inconel, and nickel having average outer-wall temperatures of 1500 F and a circumferential temperature gradient of 20 F

Preliminary free-flight investigation of the zero-lift drag penalties of several missile nose shapes for infrared seeking devices

Preliminary investigation of a rectangular supersonic scoop inlet with swept sides designed for low drag at a Mach number of 2.7

Preliminary free-flight investigation of the effects of rivets and lap joints on the drag of bodies at zero lift at supersonic Mach numbers to 2.1

A preliminary gust-tunnel investigation of leading-edge separation on swept wings


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