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- A variational theorem for creep with applications to plates and columns
- Thermal relations for two-phase expansion with phase equilibrium and example for combustion products of boron-containing fuel
- On flow of electrically conducting fluids over a flat plate in the presence of a transverse magnetic field
- Investigation of the compressive strength and creep of 7075-T6 aluminum-alloy plates at elevated temperatures
- Investigation of deflectors as gust alleviators on a 0.09-scale model of the Bell X-5 airplane with various wing sweep angles from 20 degrees to 60 degrees at Mach numbers from 0.40 to 0.90
- Free-flight investigation to determine some effects of tail damping and wing-tail interference on the rolling effectiveness of ailerons and a spoiler on a modified-delta wing at Mach numbers from 0.6 to 1.5
- Material compatibility with gaseous fluorine
- Ditching investigations of dynamic models and effects of design parameters on ditching characteristics
- Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 3: experimental performance with two stator configurations designed to eliminate blade wakes and secondary-flow effects and conclusions from entire sta
- Performance of a supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary-layer removal : Mach number range 1.5 to 2.0
- Permeability variation of a taper-rolled wire cloth
- A phenomenological relation between stress, strain rate, and temperature for metals at elevated temperatures
- Investigation at low speeds of deflectors and spoilers as gust alleviators on a model of the Bell X-5 airplane with 35 degree swept wings and on a high-aspect-ratio 35 degree swept-wing-fuselage model
- Investigation of conditions for spontaneous ignition and combustion efficiency of pentaborane in a small-scale combustor
- Charts for estimating the effects of short-period stability characteristics on airplane vertical-acceleration and pitch-angle response in continuous atmospheric turbulence
- Effect of fuselage length and a canopy on the static longitudinal and lateral stability characteristics of 45 degrees sweptback airplane models having fuselages with square cross sections
- The effect of body contouring on the longitudinal characteristics at Mach numbers up to 0.92 of a wing-fuselage-tail and several wing-fuselage combinations having sweptback wings of relatively high aspect ratio
- Effect of burner design variables on performance of 16-inch diameter ram-jet combustor using gaseous-hydrogen fuel
- Fatigue-crack propagation and residual static strength of built-up structures
- An investigation of discharge and thrust characteristics of flapped outlets for stream Mach numbers from 0.40 to 1.30
- Charts for the analysis of flow in a whirling duct
- Investigation of effectiveness of a wing equipped with a 50-percent-chord sliding flap, a 30-percent-chord slotted flap, and a 30-percent-chord slat in deflecting propeller slipstreams downward for vertical take-off
- External interference effects of a flow through static-pressure orifices of a NACA airspeed head at a Mach number of 3
- Ground simulator studies of the effects of valve friction, stick friction, flexibility, and backlash on power control system quality
- Experimental investigation of the simulation of atmospheric entry of ballistic missiles
- Effects of airplane flexibility on wing bending strains in rough air
- The effects of boundary-layer separation over bodies of revolution with conical tail flares
- Effects of airplane flexibility on wing strains in rough air at 5,000 feet as determined by flight tests of a large swept-wing airplane
- Effects of blade plan form on free-space oscillating pressures near propellers at flight Mach numbers to 0.72
- Free-flight investigation of jet effects at low supersonic Mach numbers on a fighter-type configuration employing a tail-boom assembly: longitudinal stability and trim
- Free-flight investigation at transonic speeds of the power-on characteristics including some effects of sonic propulsive jets of a four-engine delta-wing configuration
- Free-flight investigation of comparative zero-lift rolling effectiveness of a leading edge and a trailing edge air-jet spoiler on an unswept wing
- Tensile properties of Inconel X sheet under rapid-heating and constant-temperature conditions
- Tensile stress-strain properties of 17-7 PH and AM 350 stainless-steel sheet at elevated temperatures
- Chemical igniters for starting jet fuel - nitric acid rockets
- A simplified method for assessing the effect of steady rolling on angle of attack and sideslip
- A theoretical and experimental study of planing surfaces including effects of cross section and plan form
- On possible similarity solutions for three-dimensional incompressible laminar boundary layers 3: similarity with respect to stationary polar coordinates for small angle variation
- An investigation at low speed of the flow over a simulated flat plate at small angles of attack using pitot-static and hot-wire probes
- A correlation of low-speed, airfoil-section stalling characteristics with Reynolds number and airfoil geometry
- Cascade investigation of a related series of 6-percent-thick guide-vane profiles and design charts
- Basic performance characteristics of several subsonic-diffuser-bypass-duct combinations for use with supersonic inlets
- Two-dimensional cascade tests of NACA 65-(C(sub zeta)(sub o))A(sub 10))10 blade sections at typical compressor hub conditions for speeds up to choking
- Preliminary investigation of dynamic lateral stability characteristics of a configuration of the North American X-15 research airplane
- Theoretical performance of liquid hydrogen and liquid fluorine as a rocket propellant for a chamber pressure of 600 pounds per square inch absolute
- A summary of the longitudinal and lateral stability and control characteristics obtained from rocket-model tests of a swept-wing fighter-type airplane at Mach numbers from 0.5 to 1.9
- Theoretical rocket performance of JP-4 fuel with mixtures of liquid ozone and fluorine
- Temperature measurements from a flight test of two wing-body combinations at 7 degree angle of attack for Mach numbers to 4.86 and Reynolds numbers to 19.2 X 10(exp 6)
- Investigation of the planing lift of a flat plate at speeds up to 170 feet per second
- Effect of bluntness on transition for a cone and a hollow cylinder at Mach 3.1