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- Flight measurements of the low-speed characteristics of a 35 degree swept-wing airplane with blowing-type boundary-layer control in the trailing-edge flaps
- The flow past an unswept-and a swept-wing-body combination and their equivalent bodies of revolution at Mach numbers near 1.0
- Full-scale wind-tunnel tests of a 35 degree sweptback-wing airplane with high-velocity blowing over the trailing-edge flaps: longitudinal and lateral stability and control
- Fundamental flame velocity, heat of combustion, and spontaneous ignition temperature of dimethylaminodiborane
- Investigation of lateral control near the stall flight tests with high-wing and low-wing monoplanes of various configurations
- Interference effects at Mach 1.9 on a horizontal tail due to trailing shock waves from an axisymmetric body with an exiting jet
- Interaction of an exhaust jet and elementary contoured surfaces located in a supersonic air stream
- Investigation of aerodynamic characteristics in pitch and sideslip of a 45 degree sweptback-wing airplane model with various vertical locations of wing and horizontal tail : static longitudinal stability and control, M = 2.01
- Investigation of a continuous normal-shock positioning control on the bypass of a supersonic inlet in combination with the J34 turbojet engine
- Initial inclination of the mixing boundary separating an exhausting supersonic jet from a supersonic ambient stream
- Initial results of a flight investigation of the wing and tail loads on an airplane equipped with a vane-controlled gust-alleviation system
- Injection principles for liquid oxygen and heptane using two-element injectors
- Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed VI: experimental performance of two-stage turbine
- An investigation of the aerodynamic characteristics at transonic Mach numbers of a swept-wing supersonic bomber configuration
- A flight evaluation of a wing-shroud-blowing boundary-layer control system applied to the flaps of an F9F-4 airplane
- Investigation of two-stage counterrotating compressor 2: first-rotor blade-element performance
- An investigation of vertical-wind-shear intensities from balloon soundings for application to airplane- and missile-response problems
- Investigation of two-stage counterrotating compressor I : design and over-all performance of transonic first compressor stage
- Investigation of vertical drag and periodic airloads acting on flat panels in a rotor slipstream
- Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed VII : experimental performance of modified two-stage turbine
- Investigation of transient pool boiling due to sudden large power surge
- Investigation of Two-Stage Counterrotating Compressor. 3: Design of Second-Stage Rotor and Preliminary Over-All Performance
- Investigation of unsteady flow past four NACA 6-percent-thick airfoil sections
- Investigation of local heat-transfer and pressure drag characteristics of a yawed circular cylinder at supersonic speeds
- A sonic-flow orifice probe for the in-flight measurements of temperature profiles of a jet engine exhaust with afterburning
- Method of calculating core dimensions of crossflow heat exchanger with prescribed gas flows and inlet and exit states
- General theory of wave-drag reduction for combinations employing quasi-cylindrical bodies with an application to swept-wing and body combinations
- Reduction of wave drag of wing-body combinations at supersonic speeds through body distortions
- Experimental investigation of a lightweight rocket chamber
- Drag interference between a pointed cylindrical body and triangular wings of various aspect ratios at Mach numbers of 1.50 and 2.02
- Regenerative-cooling studies in a 5000-pound-thrust liquid-oxygen - JP-4 rocket engine operated at 6000-pounds-per-square-inch combustion-chamber pressure
- Performance of a blunt-lip side inlet with ramp bleed, bypass, and a long constant-area duct ahead of the engine : Mach number 0.66 and 1.5 to 2.1
- Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
- Investigation of spoiler-slot-deflector ailerons and other spoiler ailerons on a 45 degree sweptback-wing--fuselage combination at Mach numbers from 0.60 to 1.03
- External-stream effects on gross thrust and pumping characteristics of ejectors operating at off-design Mach numbers
- Full-scale evaluation of some flameholder design concepts for high-inlet-velocity afterburners
- Performance of supersonic ramp-type side inlet with combinations of fuselage and inlet throat boundary-layer removal
- The origin and distribution of supersonic interference from measurement of individual forces on several wing-fuselage-store configurations VI : swept-wing heavy-bomber configuration with stores of different sizes and shapes
- Oscillating hinge moments and flutter characteristics of a flap-type control surface on a 4-percent-thick unswept wing with low aspect ratio at transonic speeds
- An optimum switching criterion for a third-order contactor acceleration control system
- Operational characteristics of RA-14 Avon turbojet engine
- A summary of NACA research on the strength and creep of aircraft structures at elevated temperatures
- Large-scale wind-tunnel tests of an airplane model with a 45 degree sweptback wing of aspect ratio 2.8 with area suction applied to trailing-edge flaps and with several wing leading-edge modifications
- Near noise field of a jet-engine exhaust II : cross correlation of sound pressures
- Near noise field of a jet-engine exhaust 1: sound pressures
- The motions of rolling symmetrical missiles referred to a body-axis system
- Comparison of several methods for obtaining the time response of linear systems to either a unit impulse or arbitrary input from frequency-response data
- Incomplete time response to a unit impulse and its application to lightly damped linear systems
- Method and tables for determining the time response to a unit impulse from frequency-response data and for determining the fourier transform of a function of time
- Aerodynamic heating of a wing as determined from a free-flight rocket-model test to Mach number 3.64