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- Altitude-wind-tunnel investigation of several afterburner configurations having moderately high burner-inlet velocities
- Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy
- Aerodynamic characteristics at Mach number of 2.01 of two cruciform missile configurations having 70 degree delta wings with length-diameter ratios of 14.8 and 17.7 with several canard controls
- The transonic characteristics of unswept wings having aspect ratios of 4, spanwise variations in thickness ratio, and variations in plan-form taper-transonic-bump technique
- Tooth-type noise-suppression devices on a full-scale axial-flow turbojet engine
- Low-speed measurement of static stability and damping derivatives of a 60 degree delta-wing model for angles of attack of 0 degrees to 90 degrees
- Low-velocity turning as a means of minimizing boundary-layer accumulations resulting from secondary flows within turbine stators
- Methods of predicting helicopter stability
- Sea-level static equilibrium performance of actual two-spool turbojet engine and comparison with hypothetical engine
- Rocket-powered-model investigation of the effects of aeroelasticity on the rolling effectiveness of an 8.06-percent-scale McDonnell F3H-1 airplane wing at Mach numbers from 0.5 to 1.4 : TED No. NACA DE 351
- Performance comparisons of Navy jet mix and MIL-F-5624A (JP-3) fuels in tubular and annular combustors / Richard J. McCafferty
- Preliminary investigation of an asymmetric swept nose inlet of circular projection at Mach number 3.85
- Preliminary investigation of pumping and thrust characteristics of full-size cooling-air ejectors at several exhaust-gas temperatures
- Stability characteristics at low speed of a variable-sweep airplane model having a partially cambered wing with several chord-extension configurations
- An assessment of the airplane drag problem at transonic and supersonic speeds
- Aspects of internal-flow-system design for helicopter propulsive units
- Influence of combustion-chamber length on afterburner performance
- Forces and moments on inclined bodies at Mach numbers from 3.0 to 6.3
- Calibration of strain-gage installations in aircraft structures for the measurement of flight loads
- Engine performance of alloy 73J turbine blades cast to predetermined grain sizes
- Effect of immersed surfaces in combustion zone on efficiency and stability of 5-inch diameter ram-jet combustor
- Forced-convection heat-transfer and pressure-drop characteristics of a closely spaced wire matrix
- A flight investigation at transonic speeds of the aerodynamic characteristics of a model having a thin unswept wing of aspect ratio 3.1
- A flight investigation at transonic speeds and small angles of attack of the aerodynamic characteristics of a model having a 45 degree sweptback wing of aspect ratio 3 with an Naca 64A006 airfoil section
- Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) V : aerodynamic load distributions for a series of four boattailed bodies
- Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) IV : aerodynamic characteristics of series of four bodies having near-parabolic noses and cylindrical afterbodies
- Forced-convection heat-transfer characteristics of molten Flinak flowing in an Inconel system
- Investigation of several double-ramp side inlets
- The effect of stick-force gradient and stick gearing on the tracking accuracy of a fighter airplane
- An experimental investigation of the flutter of several wings of varying aspect ratio, density, and thickness ratio at Mach numbers from 0.60 to 1.10
- Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers IV : stage and blade-row performance of stage with axial-discharge stators
- Evaluation at supersonic speeds of twin-duct side-intake system with two-dimensional double-shock inlets
- Preliminary investigation of the 'freeze-casting' method for forming refractory powders
- A preliminary investigation of the use of circulation control to increase the lift of a 45 degree sweptback wing by suction through trailing-edge slots
- Kinetic study of mass transfer by sodium hydroxide in nickel under free-convection conditions /by Don R. Mosher and Robert A. Lad
- A study of the radiation from laminar and turbulent open propane-air flames as a function of flame area, equivalence ratio, and fuel flow rate
- Study of the physical properties of petrolatum-stabilized magnesium-hydrocarbon slurry fuels
- Study of the attack of an automatically controlled interceptor on a maneuvering bomber with emphasis on proper coordination of lift-acceleration and roll-angle commands during rolling maneuvers
- Preliminary performance data for the J57-P-1 turbojet engine at altitudes up to 65,000 feet
- A revised gust-load formula and a re-evaluation of v-g data taken on civil transport airplanes from 1933 to 1950
- Rocket-model investigation of the longitudinal stability and drag characteristics of a 1/10-scale model of the Convair XF2Y-1 airplane having open ducts and the elevons deflected upward 3.5 degrees : TED No. NACA DE 375
- Analytical and experimental studies of a divided-flow ram-jet combustor
- Analysis of the turbojet for propulsion of supersonic bombers
- Analytical determination of effect of turbine cooling-air-impeller performance on engine performance and comparison of experimentally determined performance of impellers with and without inducer vanes
- Wind-tunnel investigation of the effect of clipping the tips of triangular wings of different thickness, camber, and aspect ratio - transonic bumb method
- Experimental heat-transfer and friction coefficients for air flowing through stacks of parallel flat plates
- Experimental influence coefficients for the deflection of the wing of a full-scale, swept-wing bomber
- Impingement of water droplets on wedges and double-wedge airfoils at supersonic speeds
- Preliminary investigation of performance of variable-throat extended-plug-type nozzles over wide range of nozzle pressure ratios
- An Investigation of the Hydrodynamic Characteristics of a 1/10-Size Powered Dynamic Model of the Martin M-267 Patrol-Type Seaplane with Two Forebody Configurations: TED No. NACA DE 376