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- Characteristics of the Langley 8-foot transonic tunnel with slotted test section
- Compressible laminar boundary layer over a yawed infinite cylinder with heat transfer and arbitrary Prandtl number
- Boron and zirconium from crucible refractories in a complex heat-resistant alloy
- Experimental determination of effects of frequency and amplitude on the lateral stability derivatives for a delta, a swept, and unswept wing oscillating in yaw
- Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds
- Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane with External Fuel Tanks, TED No. NACA AD 3112
- Investigation of Incipient Spin Characteristics of a 1/35-Scale Model of the Convair F-102A Airplane, Coord. No. AF-AM-79
- Theory of self-excited mechanical oscillations of helicopter rotors with hinged blades
- A wind-tunnel investigation of the aerodynamic characteristics of a full-scale supersonic-type three-blade propeller at Mach numbers to 0.96
- Theoretical analysis of total-pressure loss and airflow distribution for tubular turbojet combustors with constant annulus and liner cross-sectional areas
- Differential equations of motion for combined flapwise bending, chordwise bending, and torsion of twisted nonuniform rotor blades
- Ground simulator studies of the effects of valve friction, stick friction, flexibility, and backwash on power control system quality
- Blowing-type boundary-layer control as applied to the trailing-edge flaps of a 35 degree swept-wing airplane
- Flight measurements of the vibration experienced by a tandem helicopter in transition, vortex-ring state, landing, approach, and yawed flight
- A flight-test study of total-pressure distortion in a thick-lipped nose inlet
- Flutter analysis of rectangular wings of very low aspect ratio
- Some numerical solutions of similarity equations for three-dimensional laminar incompressible boundary-layer flows
- Full-scale wind-tunnel tests of a 35 degree sweptback-wing airplane with blowing from the shroud ahead of the trailing-edge flaps
- Internal-friction study of aluminum alloy containing 4 weight percent copper
- Internal characteristics and performance of several jet deflectors at primary-nozzle pressure ratios up to 3.0
- Experimental investigation of flutter and divergence characteristics of the rocket-motor fin of the ASROC missile: COORD. No. N-AM-66
- Internal characteristics and performance of an aerodynamically controlled, variable-discharge convergent nozzle
- A method for rapid selection of design characteristics of 1-, 1 1/2-, and 2-stage turbines with optimum annulus taper
- Investigation of the aerodynamic characteristics of a model of a supersonic bomber configuration with a swept and an unswept wing at Mach numbers from 1.79 to 2.67
- Investigation of two-stage counterrotating compressor IV : over-all performance of compressor with modified second-stage rotor
- An investigation of supersonic store interference in the vicinity of a 22 degree swept-wing-fuselage configuration at Mach numbers of 1.61 and 2.01
- An investigation of some phenomena relating to aural detection of airplanes
- A method for the calculation of wave drag on supersonic-edged wings and biplanes
- A method for the calculation of the lateral response of airplanes to random turbulence
- Exploratory wind-tunnel investigation at high subsonic and transonic speeds of jet flaps on unswept rectangular wings
- A phenomenological relation between stress, strain rate, and temperature for metals at elevated temperatures
- Performance of five short multielement turbojet combustors for hydrogen fuel in quarter-annulus duct
- Performance of JP-4 fuel with fluorine-oxygen mixtures in 1000-pound-thrust rocket engines
- A nonlinear theory for predicting the effects of unsteady laminar, turbulent, or transitional boundary layers on the attenuation of shock waves in a shock tube with experimental comparison
- Noise survey under static conditions of a turbine-driven full-scale modified supersonic propeller with an advance ratio of 3.2
- Natural convection inside a flat rotating container
- Effect of the proximity of the wing first-bending frequency and the short-period frequency on the airplane dynamic-response factor
- Preliminary survey of possible methods for hypersonic aircraft
- A preliminary study of the effect of boric oxide deposits on the performance of two selected turbine stator-blade shapes
- Preliminary transonic flutter investigation of models of T-tail of Blackburn NA-39 airplane
- Preliminary heat-transfer studies on two bodies of revolution at angle of attack at a Mach number of 3.12
- Effect of leading-edge-flap deflection on the wing loads, load distributions , and flap hinge moments of the Douglas X-3 research airplane at transonic speeds
- Preliminary flight survey of fuselage and boundary-layer sound-pressure levels
- Procedure for calculating flutter at high supersonic speed including camber deflections, and comparison with experimental results
- Large-scale wind-tunnel tests of an airplane model with an unswept, aspect-ratio-10 wing, two propellers, and area-suction flaps
- Local isotropy in turbulent shear flow
- Longitudinal stability and control characteristics at Mach numbers of 1.41 and 2.01 of a 67 degree swept-wing airplane configuration with canard control surfaces
- Local instability of the elements of a truss-core sandwich plate
- Low-speed cascade investigation of compressor blades having loaded leading edges
- Low-speed experimental determination of the effects of leading-edge radius and profile thickness on static and oscillatory lateral stability derivatives for a delta wing with 60 degrees of leading-edge sweep