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- Aerodynamic performance of several techniques for spike-position control of a blunt-lip nose inlet having internal contraction; Mach numbers of 0.63 and 1.5 to 2.0
- Aerodynamic characteristics at Mach number of 4.06 of a typical supersonic airplane model using body and vertical-tail wedges to improve directional stability
- An experimental hydrodynamic investigation of the inception of vortex ventilation
- Effects of rapid heating on strength of airframe components
- Generalized master curves for creep and rupture
- Experimental evaluation of 'swirl-can' elements for hydrogen-fuel combustor
- Experimental influence coefficients and vibration modes of a built-up 45 degree delta-wing specimen
- Free-flight performance of a rotating-vane-spoiler roll control system with low actuating forces
- Hydrodynamic investigation of a model of a supersonic multijet water-based aircraft with engines exhausting from the step
- Investigation of an afterburning ramjet using gaseous hydrogen as fuel at Mach number of 3.0
- Investigation of an underslung scoop inlet at Mach numbers to 1.99
- Investigation of axially symmetric flow over steps at transonic speeds with comparisons of estimated and experimental drag results
- Investigation of an underslung normal-wedge inlet at free-stream Mach numbers from 1.50 to 1.99
- Cooling performance and structural reliability of a modified corrugated-insert air-cooled turbine blade with an integrally cast shell and base
- Static strength of cross-grain 7075-T6 aluminum-alloy extruded bar containing fatigue cracks
- Effect of spanwise variations in gust intensity on the lift due to atmospheric turbulence
- A collection of data for zero-lift damping in roll of wing-body combinations as determined with rocket-powered models equipped with roll-torque nozzles
- Effects of conical camber on the lift, drag, and pitching-moment characteristics of a triangular wing of aspect ratio 3.0
- Effects of extreme surface cooling on boundary-layer transition
- A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed
- Effect of interstage bleed on rotating stall and blade vibration in a 13-stage axial-flow compressor in a turbojet engine
- The design and cascade tests of free-streamline and full-contour 160 degrees turning supersonic-turbine-blade sections
- Design and experimental investigation of a single-stage turbine with a downstream stator
- Design and test of mixed-flow impellers 8: comparison of experimental results for three impellers with shroud redesigned by rapid approximate method
- The interrelated effects of engine rotor momentum and flight regime on the dynamic stability of high-performance aircraft
- Effects of vertical location of wing and horizontal tail on the aerodynamic characteristics in pitch at Mach numbers from 0.60 to 1.40 of an airplane configuration with an unswept wing
- Effects of wing-mounted external stores on the longitudinal and lateral handing qualities of the Douglas D-558-II research airplane
- Effects of wing warp on the lift, drag, and static longitudinal stability characteristics of an aircraft configuration having an arrow wing of aspect ratio 1.86 at Mach numbers from 1.1 to 1.7
- Analysis of shock motion in ducts during disturbances in downstream pressure
- A hydrogen peroxide turbojet-engine simulator for wing-tunnel powered-model investigations
- Experimental investigation of dynamic relations in a 48-inch ram-jet engine
- The application of matrix methods to coordinate transformations occurring in systems studies involving large motions of aircraft
- An analog computer study of several stability augmentation schemes designed to alleviate roll-induced instability
- Application of obliquely mounted strain gage to measurement of residual stresses in disks
- A balanced-pressure sliding seal used for transfer of pressurized air between stationary and rotating parts
- Base pressure at supersonic speeds on two-dimensional airfoils and on bodies of revolution with and without fins having turbulent boundary layers
- Investigation of semivaneless turbine stator designed to produce axially symmetrical free-vortex flow
- Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study 2: design and experimental performance of turbine with low-velocity-turning stator and standard rotor
- Jet effects on base pressures of conical afterbodies at Mach 1.91 and 3.12
- Static longitudinal and lateral stability characteristics at low speed of 45 degree sweptback-midwing models having wings with an aspect ratio of 2, 4, or 6
- Wind-tunnel investigation of external-flow jet-augmented double slotted flaps on a rectangular wing at an angle of attack of 0 degree to high momentum coefficients
- Wind-tunnel investigation of effect of propeller slipstreams on aerodynamic characteristics of a wing equipped with a 50-percent-chord sliding flap and a 30-percent-chord slotted flap
- Wind-tunnel investigation of effects of ground proximity and of split flaps on the lateral stability derivatives of a 60 degree delta-wing model oscillating in yaw
- Some experiments at high supersonic speeds on the aerodynamic and boundary-layer transition characteristics of high-drag bodies of revolution
- Investigation of boundary-layer transition on flat-faced bodies of revolution at high supersonic speeds
- Performance comparison at Mach numbers 1.8 and 2.0 of full-scale and quarter-scale translating-spike inlets
- Analysis of two-stage-turbine efficiency characteristics in terms of work and speed requirements
- Analysis of efficiency characteristics of a single-stage turbine with downstream stators in terms of work and speed requirements
- Investigation of a supersonic-inlet - turbojet-engine combination at Mach 2.0 and angles of attack up to 6 degrees
- Use of main-inlet bypass to supply ejector exhaust nozzle at supersonic speeds