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- Tests of a small-scale NACA submerged inlet at transonic Mach numbers
- An investigation of several NACA 1-series nose inlets with and without protruding central bodies at high-subsonic Mach numbers and at a Mach number of 1.2
- Investigation of a simple device for preventing separation due to shock and boundary-layer interaction
- Flight investigation at Mach numbers from 0.6 to 1.7 to determine drag and base pressures on a blunt-trailing-edge airfoil and drag of diamond and circular-arc airfoils at zero lift
- Low-speed wind-tunnel investigation of a triangular sweptback air inlet in the root of a 45 degree sweptback wing
- Lateral-control investigation of flap-type controls on a wing with quarter-chord line sweptback 35©�, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section.Transonic-bump method
- Aerodynamic investigation at Mach number 1.92 of a rectangular wing and tail and body configuration and Its components
- Flight determination of the drag and pressure recovery of an NACA 1-40-250 nose inlet at Mach numbers from 0.9 to 1.8
- Results of two free-fall experiments on flutter of thin unswept wings in the transonic speed range
- Aerodynamic characteristics of a leading-edge slat on a 35 degree swept-back wing for Mach numbers from 0.30 to 0.88
- An investigation at transonic speeds of the effects of thickness ratio and of thickened root sections on the aerodynamic characteristics of wings with 47©� sweepback, aspect ratio 3.5, and taper ratio 0.2 in the slotted test section of the Langley 8-foot high-speed tunnel
- Miscellaneous directional-stability data for several airplane-like configurations from rocket-model tests at transonic speeds
- Factors affecting transition at supersonic speeds
- Fuel characteristics pertinent to the design of aircraft fuel systems.Supplement 1 - Additional information on MIL-F-7914(AER) Grade JP-5 fuel and several fuel oils
- Supersonic flutter of a 60©� delta wing encountered during the flight test of a rocket-propelled model
- Normal force, center of pressure, and zero-lift drag of several ballistic-type missiles at Mach numbers of 4.05
- Some effects of external wing tip stores on the rolling effectiveness and drag of plain and half-delta tip ailerons on a 4-percent-thick tapered, unswept wing
- Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0.18 chord
- Effects of some external-store mounting arrangements and store shapes on the buffet and drag characteristics of wingless rocket-powered models at Mach numbers from 0.7 to 1.4
- Effects of overhang balance on the hinge-moment and effectiveness characteristics of an unswept trailing-edge control on a 60 degree delta wing at transonic and supersonic speeds
- Statistical survey of icing data measured on scheduled airline flights over the United States and Canada from November 1951 to June 1952
- A survey of methods for turbojet thrust measurement applicable to flight installation
- Combustion of aluminum borohydride in a supersonic wind tunnel
- The rolling moment due to sideslip of swept wings at subsonic and transonic speeds
- An experimental study of a method of designing the sweptback-wing - fuselage juncture for reducing the drag at transonic speeds
- Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5
- Effect of surface roughness on characteristics of spherical shock waves
- Some observations on loss of static strength due to fatigue cracks
- Preliminary investigation of the failure of pressurized stiffened cylinders
- Preliminary investigation of the compressive strength and creep lifetime of 2024-T3 (formerly 24S-T3) aluminum-alloy plates at elevated temperatures
- Tensile properties of some sheet materials under rapid-heating conditions
- A study of the response of panels to random acoustic excitation
- A free-flight investigation of the effects of simulated sonic turbojet exhaust on the drag of a boattail body with various jet sizes from Mach number 0.87 to 1.50
- Free-flight measurements of aerodynamic heat transfer to Mach number 3.9 and of drag to Mach number 6.9 of a fin-stabilized cone-cylinder configuration
- Initial experimental investigation of the aerodynamic load on the wing of a model caused by a blast-induced gust that increases the angle of attack into the stall region
- Vertical and drag ground-reaction forces developed in landing impacts of a large airplane
- Experimental aerodynamic forces and moments at low speed of a missile model during simulated launching from the midsemispan location of a 45 degree sweptback wing-fuselage combination
- Theoretical analysis of the longitudinal behavior of an automatically controlled supersonic interceptor during the attack phase against maneuvering and nonmaneuvering targets
- Transonic wind-tunnel investigation of the effects of sweepback and thickness ratio on the wing loads of a wing-body combination of aspect ratio 4 and taper ratio 0.6
- Aerodynamic characteristics in pitch of several triple-body missile configurations at Mach numbers 0.6 to 1.4
- Correlation of flight and analog investigations of roll coupling
- Preliminary attempts at isothermal compression of a supersonic air stream
- Investigation at supersonic and subsonic Mach numbers of auxiliary inlets supplying secondary air flow to ejector exhaust nozzles
- Effect of diameter of closed-end coolant passages on natural-convection water cooling of gas-turbine blades
- Criteria for initial flow reversal in symmetrical twin-intake air-induction systems operating at supersonic speeds
- Visual study of free convection in a narrow vertical enclosure
- Internal performance characteristics of short convergent-divergent exhaust nozzles designed by the method of characteristics
- An analog study of a shock-position diffuser control on a supersonic turbojet engine
- Some recent research on the handling qualities of airplanes
- Flight determination of drag and pressure recovery of two scoop inlets located at maximum-body-diameter station at Mach numbers from 0.8 to 1.8