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- Longitudinal aerodynamic characteristics to large angles of attack of a cruciform missile configuration at a Mach number of 2
- A low-speed investigation of the aerodynamic, control, and hinge-moment characteristics of two types of controls and balancing tabs on a large-scale thin delta-wing-fuselage model
- Measurement of heat-transfer and friction coefficients for flow of air in noncircular ducts at high surface temperatures
- Measurements of normal-force-coefficient fluctuation on four 9-percent-thick airfoils having different locations of maximum thickness
- Effect of ignitor design and ignitor spark-gap environment on ignition in a turbojet combustor
- Ignition of ammonia and mixed oxides of nitrogen in 200-pound-thrust rocket engines at 160 F
- Comparison of Experimental Hydrodynamic Impact Loads and Motions for a V-Step and a Transverse-Step Hydro-Ski
- On traveling waves in beams
- Comparison of normal load factors experienced with jet fighter airplanes during combat operations with those of flight tests conducted by the NACA during operational training
- Effect of channel geometry on the quenching of laminar flames
- A study of the use of controls and the resulting airplane response during service training operations of four jet fighter airplanes
- Correlation of isothermal contours formed by penetration of jet of liquid ammonia directed normal to an airstream
- Drag data for 16-inch-diameter ram-jet engine with double-cone inlet in free flight at Mach numbers from 0.7 to 1.8
- Design and test of mixed-flow impellers 4: experimental results for impeller models MF-1 and MF-2 with changes in blade height
- Effect of nozzle contour on drag of parabolic afterbodies
- Aerodynamic characteristics of several tip controls on a 60 degree wing at a Mach number of 1.61
- Aerodynamic characteristics of two flat-bottomed bodies at Mach number of 3.12
- Analytical study of losses at off-design conditions for a fixed geometry turbine
- Angle-of-attack-supersonic performance of a configuration consisting of a ramp-type scoop inlet located either on top or bottom of a body of revolution
- Analytical investigation of off-design performance of a transonic turbine
- The aerodynamic characteristics of two series of lifting bodies at Mach number 6.86
- Buffeting forces on two-dimensional airfoils as affected by thickness and thickness distribution
- Comparison of experimental with calculated results for the lifting effectiveness of a flexible 45 degree sweptback wing of aspect ratio 6.0 at Mach numbers from 0.8 to 1.3
- Comparison of effects of ailerons and combinations of spoiler-slot-deflector arrangements on spin recovery of sweptback-wing model having mass distributed along the fuselage
- Analysis of performance of four symmetrical-diagram-type subsonic inlet-stage axial-flow compressors
- Aerodynamic characteristics of several flap-type trailing-edge controls on a trapezoidal wing at Mach numbers of 1.61 and 2.01
- A comparison of flight measurements with calculations of the horizontal-tail root bending moments for a jet-powered bomber airplane
- Comparison of low-speed rotor and cascade performance for medium-camber NACA 65-(C(sub lo)A(sub 10) 10 compressor-blade sections over a wide range of rotor blade-setting angles at solidities. of 1.0 and 0.5
- Analysis of off-design operation of high Mach number supersonic turbojet engines
- Characteristics of a hydraulic control determined from transient data obtained with a turbojet engine at altitude
- Characteristics of flow about axially symmetric isentropic spikes for nose inlets at Mach number 3.85
- Combined compressor coolant injection and afterburning for turbojet thrust augmentation
- Combustion performance of two experimental turbojet annular combustors at conditions simulating high-altitude supersonic flight
- Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines II : analytical techniques
- Blow-out velocities of various petroleum, slurry, and hydride fuels in a 1 7/8-inch diameter combustor
- 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