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- Effect of water on carbon monoxide-oxygen flame velocity
- Effect of unequal air-flow distribution from twin inlet ducts on performance of an axial-flow turbojet engine
- The effect of magnesium particles of various equivalent diameters on some physical properties of petrolatum-stabilized magnesium-hydrocarbon slurries
- Effect of wing flexibility on the damping roll of a notched delta-wing body combination between Mach numbers 0.6 and approximately 2.2 as determined with rocket-propelled models
- The Effect of Wing Profile on the Transonic Characteristics of Rectangular and Triangular Wings Having Aspect Ratios of 3: Transonic Bump Technique
- Effect of rotation of a NACA 1-series E-type cowling on the internal flow and force characteristics of the cowling at Mach numbers up to 0.84 and at an angle of attack of 0 degrees
- Experimental and calculated static characteristics of a two-blade NACA 10-(3)(062)-045 propeller
- An evaluation of turbojet engine thrust control by exhaust-nozzle-area modulation and compressor-inlet throttling
- Summary of the lift, drag, and stability of 1/10-scale rocket-boosted models of the McDonnell XF3H-1 airplane for a Mach number range of 0.6 to 1.4 as affected by the operation of extensible rocket racks : TED No. NACA DE 351
- Effect of wing slats and inboard wing fences on the longitudinal stability characteristics of the DOUGLAS D-558-II airplane in accelerated maneuvers at subsonic and transonic speeds
- Effects of leading-edge chord extensions and an all-movable horizontal tail on the aerodynamic characteristics of a wing-body combination employing a triangular wing of aspect ratio 3 mounted in a high position at subsonic and supersonic speeds
- Effects of multiaxial stretching on crazing and other properties of transparent plastics
- Effects of molecular weight on crazing and tensile properties of polymethyl methacrylate
- Effectiveness of boundary-layer removal near throat of ramp-type side inlet at free-stream Mach number of 2.0
- Effect on transonic and supersonic drag of fuselage gloves designed to give a smooth overall area distribution to a swept-wing--body combination
- Effect on the low-speed aerodynamic characteristics of a 49 degree sweptback wing having an aspect ratio of 3.78 of blowing air over the trailing-edge flap and aileron
- Evaluation of Altitude-Ignition Characteristics of Three Fuels of Different Volatility in a Turbojet Engine
- Effects of two spinner shapes on the pressure recovery in an NACA 1-series D-type cowl behind a three-blade propeller at Mach numbers up to 0.80
- Experimental determination of boundary-layer transition on a body of revolution at M = 3.5
- Experimental data for four full-scale conical cooling-air ejectors
- Experimental determination of aerodynamic forces normal to the chord due to rotating stall acting on compressor blading
- An experimental investigation of four triangular-wing-body combinations in sideslip at Mach numbers 0.6, 0.9, 1.4, and 1.7
- Experimental investigation of control signals and the nature of stall and surge behavior in a turbojet engine
- Experimental investigation of effect of high-aspect-ratio rotor blades on performance of conservatively designed turbine
- Experimental investigation of the effect of a shrouded rotor on the performance of a conservatively designed turbine
- Experimental investigation of the effect of fuel-injection-system design variables on afterburner performance
- Experimental investigation of the aerodynamic characteristics of a ballistic-type missile
- Aerodynamic characteristics at transonic and supersonic speeds of a rocket-propelled airplane configuration having a 52.5 degree delta wing and a low, swept horizontal tail
- Aerodynamic characteristics including effects of wing fixes of a 1/20-scale model of the Convair F-102 airplane at transonic speeds
- Aerodynamic characteristics of a cruciform-wing missile with canard control surfaces and of some very small span wing-body missiles at a Mach number of 1.41
- Aerodynamic characteristics of a full-span trailing-edge control on a 60 degree delta wing with and without a spoiler at Mach number 1.61
- Effect of inlet-annulus area blockage on over-all performance and stall characteristics of an experimental 15-stage axial-flow compressor
- Multiple over-all performance and rotating-stall characteristics of a 15-stage experimental axial-flow compressor at an intermediate speed
- Summary of rocket-model tests at zero lift of an arrow-wing missile configuration from Mach numbers of 0.9 to 1.8
- Results of free-flight test of 1/10-scale model of the Convair XF2Y-1 airplane between Mach numbers of 0.7 and 1.45, including power-on flight at Mach number 1.2 : TED No. NACA DE 365
- Shock-turbulence interaction and the generation of noise
- Some screeching-combustion characteristics of a transpiration-cooled afterburner having a porous wall of wire cloth
- Some observations of shock-induced turbulent separation on supersonic diffusers
- Some internal-flow characteristics of several axisymmetrical NACA 1-series nose air inlets at zero flight speed
- Starting and performance characteristics of a large asymmetric supersonic free-jet facility
- Starting characteristics and combustion performance of magnesium slurry in 6.5-inch-diameter ram-jet engine mounted in connected-pipe facility
- Pumping and thrust characteristics of several divergent cooling-air ejectors and comparison of performance with conical and cylindrical ejectors
- Tests in the Ames 40- by 80-foot wind tunnel of the aerodynamic characteristics of airplane models with plain spoiler ailerons
- The effects of wing-mounted external stores on the trim, buffet, and drag characteristics of a rocket-propelled model having a 45 degree sweptback wing
- Experimental performance of liquid fluorine-liquid ammonia propellant combination in 1000-pound-thrust rocket engines
- Effect of a wing leading-edge flap and chord-extension on the high subsonic control characteristics of a spoiler-slot-deflector control located at two spanwise positions
- Effects of high-lift devices and horizontal-tail location on the low-speed characteristics of a large-scale 45 degree swept-wing airplane configuration
- Investigation of the effects of profile shape on the aerodynamic and structural characteristics of thin, two-dimensional airfoils at supersonic speeds
- Flight investigation of the effects of horizontal-tail height, moment of inertia, and control effectiveness on the pitch-up characteristics of a 35 degree swept-wing fighter airplane at high subsonic speeds
- Flight investigation of the effects of a partial-span leading-edge chord extension on the aerodynamic characteristics of a 35 degree swept-wing fighter airplane