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- Investigation at supersonic speeds of a translating-spike inlet employing a steep-lip cowl
- Thrust characteristics of a series of convergent-divergent exhaust nozzles at subsonic and supersonic flight speeds
- Pumping and drag characteristics of an aircraft ejector at subsonic and supersonic speeds
- Tests in the Ames 40- by 80-foot wind tunnel of the aerodynamic characteristics of airplane models with plain spoiler ailerons
- On slender-body theory at transonic speeds
- 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 - longitudinal stability and control
- Preliminary investigation of performance and starting characteristics of liquid fluorine: Liquid oxygen mixtures with jet fuel
- Method of designing corrugated surfaces having maximum cooling effectiveness within pressure-drop limitations for application to cooled turbine blades
- Analysis of a nuclear-powered ram-jet missile
- Force Measurements on Cone-Cylinder Body of Revolution with Various Nose and Fin Configurations at Mach Number 4.0
- Performance of a pair of tubular combustors with an external pilot chamber
- Performance characteristics of several short annular diffusers for turbojet engine afterburners
- Performance of a supersonic ramp inlet with internal boundary-layer scoop
- Performance of slurries of 50 percent boron in JP-4 fuel in 5-inch ram-jet burner
- Investigation at high subsonic speeds of finned and unfinned bodies mounted at various locations from the wings of unswept- and swept-wing--fuselage models, including measurements of body loads
- An investigation at high subsonic speeds of the pressure distributions on a 45 degree sweptback vertical tail in sideslip with and without a 45 degree sweptback horizontal tail located on the fuselage center line
- Investigation of compressible flow mixing losses obtained downstream of a blade row
- Investigation at high subsonic speeds of the effect of adding various combinations of missiles on the aerodynamic characteristics of sweptback and unswept wings combined with a fuselage
- Investigation at high subsonic speeds of the pressure distributions on a 45 degree sweptback horizontal tail mounted at 50-percent and 100-percent vertical-tail span
- Effects of additives on corrosion and mass transfer in sodium hydroxide - nickel systems under free-convection conditions
- Dynamic corrosion of nickel at 1500 F by sodium hydroxide with various additives in a torrid circulating apparatus
- Dynamic corrosion in an iron - stainless steel toroid by sodium at 900 F
- Investigation of effect of number and width of annular flame-holder gutter on afterburner performance
- Explosion and combustion properties of alkylsilanes I : temperature-composition limits of explosion for methyl-,dimethyl-,trimethyl-,tetramethyl-,and vinylsilane at atmospheric pressure
- Cooling characteristics of a transpiration-cooled afterburner with a porous wall of brazed and rolled wire cloth
- Ground tests of the elevator power control system and feel device in a Boeing B-47A airplane
- Effects of angle of attack and airfoil profile on the two-dimensional flutter derivatives for airfoils oscillating in pitch at high subsonic speeds
- Effects of airfoil profile on the two-dimensional flutter derivatives for wings oscillating in pitch at high subsonic speeds
- Chordwise pressures and section moment force and moment coefficients at high subsonic speeds near midspan of a tapered 35 degree sweptback wing with a flap-type control and an attached tab
- The effect of lip shape on a nose-inlet installation at Mach numbers from 0 to 1.5 and a method for optimizing engine-inlet combinations
- Free-flight investigation of the full-scale Hughes Falcon missile, D configuration, to determine aileron effectiveness and damping in roll
- Free-flight tests of 45 degree swept wings of aspect ratio 3.15 and taper ratio 0.54 to measure wing damping of the first bending mode and to investigate the possibility of flutter at transonic speeds
- Effect of nose shape and trailing-edge bluntness on the aerodynamic characteristics of an unswept wing of aspect ratio 3.1, taper ratio 0.4, and 3-percent thickness
- Effect of a leading-edge flap upon the lift, drag, and pitching moment of an airplane employing a thin, unswept wing
- Effects of diffuser and center-body length on performance of annular diffusers with constant-diameter outer walls and with vortex-generator flow controls
- Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance
- Effects of base bleed on the base pressure of blunt-trailing-edge airfoils at supersonic speeds
- Free-flight zero-lift drag-rise measurements of equivalent bodies of revolution of several versions of the Douglas XF4D-1 airplane at transonic speeds: TED No. NACA AD 394
- Experimental investigation of drag of afterbodies with exiting jet at high subsonic Mach numbers
- Cascade investigation of a related series of 6-percent-thick guide-vane profiles and design charts
- Drag and longitudinal trim characteristics of a low-tail version of the North American YF-100A airplane as determined from the flight test at low lift of a 0.11-scale rocket-powered model at Mach numbers between 0.75 and 1.78
- Minimum drag of 0.11-scale rocket-powered models of the Chance Vought XF8U-1 airplane, with and without nose modifications, at Mach numbers between 0.85 and 1.30 : TED No. NACA DE 392
- A summary of the drag and longitudinal trim at low lift of the North American YF-100A airplane at Mach numbers from 0.75 to 1.77 as determined by flight tests of 0.11-scale rocket models
- Altitude investigation of 20-inch-diameter ram-jet engine with annular-piloted combustor
- Performance of a vaporizing annular turbojet combustor at simulated high altitudes
- Preliminary investigation of an annular turbojet combustor having a catalytic-coated liner
- A comparison of the longitudinal aerodynamic characteristics at Mach numbers up to 0.94 of swept back wings having NACA 4-digit or NACA 64A thickness distributions
- Summary of some rocket-model investigations of effects of wing aspect ratio and thickness on aileron rolling effectiveness including some effects of spanwise aileron location for sweptback wings with aspect ratio of 8
- Some effects of aileron span, aileron chord, and wing twist on rolling effectiveness as determined by rocket-powered model tests and theoretical estimates
- Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data