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- Tests of a centering spring used as an artificial feel device on the elevator of a fighter airplane
- Experimental investigation of air-cooled turbine blades in turbojet engine 11: internal-strut-supported rotor blade
- Effects of stabilizing fins and a rear-support sting on the base pressure of a body of revolution in free flight at Mach numbers from 0.7 to 1.3
- Effects of wing elasticity on the aerodynamic characteristics of a 45 degree sweptback-wing-fuselage combination measured in the Langley 8-foot transonic tunnel
- The effects of oscillation amplitude and frequency on the experimental damping in pitch of a triangular wing having an aspect ratio of 4
- Effects of plan form, airfoil section, and angle of attack on the pressures along the base of blunt-trailing-edge wings at Mach numbers of 1.41, 1.62, and 1.96
- Effects of horizontal-tail position and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degree triangular-wing model having twin triangular all-movable tails
- Effects of finite span on the section characteristics of two 45 degree swept-back wings of aspect ratio 6
- Free-flight-tunnel investigation of the dynamic lateral stability and control characteristics of a high-aspect-ratio bomber model with a sweptback-wing fighter model attached to each wing tip
- A summary and analysis of the low-speed longitudinal characteristics of swept wings at high Reynolds number
- A summary and analysis of the low-speed longitudinal characteristics of swept wings at high Reynolds number
- A transonic wind-tunnel investigation of the effects of nacelle shape and position on the aerodynamic characteristics of two 47 degree sweptback wing-body configurations
- A transonic wind-tunnel investigation of the characteristics of a twisted and cambered 45 degree sweptback wing-fuselage configuration
- Summary of methods for calculating dynamic lateral stability and response and for estimating aerodynamic stability derivatives
- Altitude performance investigation of single- and double-annular turbojet-engine combustors with various size fuel nozzles
- Altitude investigation of three flame-holder and fuel-systems configurations in a short converging afterburner on a turbojet engine
- The transonic characteristics of 38 cambered rectangular wings of varying aspect ratio and thickness as determined by the transonic-bump technique
- Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds : aspect-ratio series
- Altitude performance of annular combustor type turbojet engine with JFC-2 fuel
- Altitude performance investigation of two flame-holder and fuel-system configurations in short afterburner
- Altitude wind tunnel investigation of high-temperature afterburners
- Two-dimensional chord-wise load distributions at transonic speeds
- An active particle diffusion theory of flame quenching for laminar flames
- Transonic aerodynamic characteristics of three thin triangular wings and a trapezoidal wing, all of low aspect ratio
- Low-speed lateral-control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 2.5 equipped with spoilers and with sharp- and thickened-trailing-edge flap-type ailerons at a Reynolds number of 7.6 x 10(exp 6)
- Low-speed longitudinal characteristics of a 45 degrees sweptback wing of aspect ratio 8 with high-lift and stall-control devices at Reynolds numbers from 1,500,000 to 4,800,000
- Low speed stability characteristics of a complete model with a wing of W plan form
- Low-speed static longitudinal stability and control characteristics of 60 degree triangular-wing and modified 60 degree triangular-wing models having half-delta and half-diamond tip controls
- Low-speed static longitudinal and lateral stability characteristics of a model with leading-edge chord-extensions incorporated on a 40 degree sweptback circular-arc wing of aspect ratio 4 and taper ratio 0.50
- Low-speed tests of a free-to-yaw model in two wind tunnels of different turbulence
- An investigation of the subsonic speed range of a full-span and a semispan model of a plane wing and of a cambered and twisted wing, all having 45 degrees of sweepback
- Preliminary air-flow and thrust calibrations of several conical Cooling-air ejectors with a primary to secondary temperature ratio of 1.0 I :diameter ratios of 1.21 and 1.10
- Solubility of water in hydrocarbons
- Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane IV : rectangular cowl inlets with two-dimensional compression ramps
- Performance and operational characteristics of a python turbine-propeller engine at simulated altitude conditions / Carl L. Meyer and Lavern A. Johnson
- Performance characteristics of canard-type missile with vertically mounted nacelle engines at Mach numbers 1.5 to 2.0
- Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 3: normal wedge inlet with semicircular cowl
- Performance characteristics of canard-type missile with wing-mounted nacelle engines at Mach numbers 1.5 to 2.0
- Recent data on controls
- Some control considerations for ram-jet engines
- Preliminary investigation of control characteristics at transonic speeds of a tapered 45 degree sweptback wing of aspect ratio 3 having a horn-balanced full-span control
- Preliminary investigation of flow fluctuations during surge and blade row stall in axial-flow compressors / c Merle C. Huppert
- Pressure recovery, drag, and subcritical stability characteristics of three conical supersonic diffusers at stream Mach numbers from 1.7 to 2.0
- Pressure limits of flame propagation of pure hydrocarbon-air mixtures at reduced pressure
- An approximation to the effect of geometric dihedral on the rolling moment due to sideslip for wings at transonic and supersonic speeds
- An analysis of the effect of structural feedback on the flutter of a control surface having a power-boost system
- Influence of a canard-type control surface on the internal and external performance characteristics of nacelle-mounted supersonic diffusers (conical centerbody) at a rearward body station for a Mach number of 2.0
- Influence of fuselage-mounted rocket boosters on flow field at inlet and on diffuser performance of strut-mounted engine at Mach numbers of 1.8 and 2.0
- Influence of fuselage and canard-type control surface on the flow field adjacent to a rearward fuselage station at a Mach number of 2.0 : data presentation
- Hinge-moment and control-effectiveness characteristics of an outboard flap with an overhang nose balance on a tapered 35 degree sweptback wing of aspect ratio 4: transonic-bump method