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- Analysis of several methods of pumping cooling air for turbojet engine afterburners
- Analytical evaluation of effect of equivalence ratio inlet-air temperature and combustion pressure on performance of several possible ram-jet fuels
- Behavior of forged S-816 turbine blades in steady-state operation of J33-9 turbojet engine with stress-rupture and metallographic evaluations
- A comparison of gust loads measured in flight on a swept-wing airplane and an unswept-wing airplane
- Component tests to determine the aerodynamic characteristics of an all-moveable 70 degree delta canard-type control in the presence of a body at a Mach number of 1.61
- Comparison of measured and predicted indicated angles of attack near the fuselages of a triangular-wing wind-tunnel model and a swept-wing fighter airplane in flight
- A transonic wind-tunnel investigation of the effects of body indentation, as specified by the transonic drag-rise rule, on the aerodynamic characteristics and flow phenomena of an unswept-wing-body combination
- Characteristics of a canard-type missile configuration with an underslung scoop inlet at Mach numbers from 1.5 to 2.0
- Effect of variations in Reynolds number on the aerodynamic characteristics of three bomb or store shapes at a Mach number of 1.62 with and without fins
- Evaporation and spreading of isooctane sprays in high velocity air streams
- The effects of leading-edge extensions, a trailing-edge extension, and a fence on the static longitudinal stability of a wing-fuselage-tail combination having a wing with 35 degrees of sweepback and an aspect ratio of 4.5
- Effective thermal conductivities of magnesium oxide stainless steel, and uranium oxide powders
- The effects of nacelles and of extended split flaps on the longitudinal characteristics of a wing-fuselage-tail combination having a wing with 40 degrees of sweepback and an aspect ratio of 10
- Estimation of water landing loads on hydro-ski-equipped aircraft
- Effects of trailing-edge bluntness on the lift, drag, and pitching-moment characteristics of unswept, 45 degree swept, and 45 degree delta wings at Mach numbers of 1.41, 1.62, and 1.96
- Experimental investigation of laminar-boundary-layer control on an airfoil section equipped with suction slots located at discontinuities in the surface pressure distribution
- Experimental investigation of physical and combustion properties of several residual fuel oils and magnesium - fuel-oil slurries in a ram-jet-type combustor
- Experimental investigation of screeching combustion in full-scale afterburner
- Experimental investigation of several water-injection configurations for turbine-blade spray cooling in a turbojet engine
- Experimental and theoretical study of the interference at low speed between slender bodies and triangular wings
- Experimental investigation of the effect of entrance width-to-height ratio on the performance of an auxiliary scoop-type inlet at Mach numbers from 0 to 1.3
- An experimental investigation of the effect of various parameters including tip Mach number on the flutter of some model helicopter rotor blades
- Experimental investigation of the effects of plan-form taper on the aerodynamic characteristics of symmetrical unswept wings of varying aspect ratio
- Aerodynamic characteristics in pitch of a series of cruciform-wing missiles with canard controls at a Mach number of 2.01
- Aerodynamic characteristics of a 68.4 degree delta wing at Mach numbers of 1.6 and 1.9 over a wide Reynolds number range
- The aerodynamic characteristics at transonic speeds of an all-movable, tapered, 45 degree sweptback, aspect-ratio-4 tail deflected about a skewed hinge axis and equipped with an inset unbalancing tab
- Aluminum borohydride as an ignition source for turbojet combustors
- Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controls
- Results of a rocket-model investigation of control-surface buzz and flutter on a 4-percent-thick unswept wing and on 6-, 9-, and 12-percent-thick swept wings at transonic speeds
- Results of measurements of maximum lift and buffeting intensities obtained during flight investigation of the Northrop X-4 research airplane
- Some fundamental aspects of nitric acid oxidants for rocket applications
- Some observations on stall flutter and buffeting
- Slotted-boundary interference effects on wedge airfoils at low supersonic Mach numbers
- Some torsional-damping measurements of laminated beams as applied to the propeller stall-flutter problem
- Static aeroelastic phenomena of M-, W-, and A-wings
- Static crucible investigation of corrosion and mass-transfer of nickel in molten sodium hydroxide with various additives
- Summary of pitch-damping derivatives of complete airplane and missile configurations as measured in flight at transonic and supersonic speeds
- Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0.33 and 0.20
- Experimental investigation of aerodynamically balanced trailing-edge control surfaces on an aspect ratio 2 triangular wing at subsonic and supersonic speeds
- An experimental study of porosity characteristics of perforated materials in normal and parallel flow
- The effect at high subsonic speeds of a flap-type aileron on the chordwise pressure distribution near midsemispan of a tapered 35 degree sweptback wing of aspect ratio 4 having NACA 65A006 airfoil section
- The effects of extensible rocket racks on lift, drag, and stability of a 1/10-scale rocket-boosted model of the McDonnell XF3H-1 airplane for a Mach number range of 0.60 to 1.34 : TED No. NACA DE 31
- Effects of high degrees of biaxial stretch forming on crazing and other properties of acrylic plastic glazing
- Effects of nitrogen tetroxide and water concentration on freezing point and ignition delay of fuming nitric acid
- Comparison of ignition delays of several propellant combinations obtained with modified open-cup and small-scale rocket engine apparatus
- Ignition delays of alkyl thiophosphites with white and red fuming nitric acids within temperature range 80 to -105 degrees Fahrenheit
- A flight investigation of the effect of leading-edge camber on the aerodynamic characteristics of a swept-wing airplane
- Investigation of 16-inch impulse-type supersonic compressor rotor with turning past axial direction
- Investigation at transonic speeds of aerodynamic characteristics of a semielliptical air inlet in the root of a 45 degree sweptback wing
- A theory for stability and buzz pulsation amplitude in ram jets and an experimental investigation including scale effects