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Over-all performance of J35-A-23 two-stage turbine
Theoretical Investigation of an Automatic Control System With Primary Sensitivity to Normal Accelerations as Used to Control a Supersonic Canard Missile Configuration
Low-Speed Investigation of the Effects of Single Slotted and Double Slotted Flaps on a 47.7 Degree Sweptback-Wing: Fuselage Combination at a Reynolds Number of 6.0 X 10(Exp 6)
Compilation and review of effects of design parameters on ditching characteristics
Solubility of water in hydrocarbons
Low-Speed Lateral-Control Investigation of a Flap-Type Spoiler Aileron With and Without a Deflector and Slot on a 6-Percent-Thick, Tapered, 45 Degree Sweptback Wing of Aspect Ratio 4
The Sodium Hydroxide Reactor: Effect of Reactor Variables on Criticality and Fuel-Element Temperature Requirements for Subsonic and Supersonic Aircraft Nuclear Propulsion
Pressure Measurements at Supersonic Speeds on a Section of a Rectangular Wing Having an NACA 65-009 Profile
Planing Characteristics of Six Surfaces Representative of Hydro-Ski Forms
A Transonic-Wing Investigation in the Langley 8-foot High-Speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-Fuselage Configuration with a Wing of 45 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section
Effect of Mach Number on Over-All Performance of Single-Stage Axial-Flow Compressor Designed for High Pressure Ratio
Investigation of altitude starting and acceleration characteristics of J47 turbojet engine
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Lateral Control Characteristics at Mach Numbers of 1.40 and 1.59
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degrees Sweepback: Estimated Downwash Angles Derived From Pressure Measurements on the Tail at Mach Numbers of 1.40 and 1.59
Experimental investigation of an axial flow compressor inlet stage operating at transonic relative inlet Mach numbers 1: over-all performance of stage with transonic rotor and subsonic stators up to rotor relative inlet Mach number of 1.1
Low-speed investigation of the effects of wing leading-edge modifications and several outboard fin arrangements on the static stability characteristics of a large-scale triangular wing
Small-scale transonic investigation of the effects of twist and camber on the aerodynamic characteristics of a 60 degrees 42' sweptback wing of aspect ratio 1.94
Studies of the flow field behind a large scale 47.5 degree sweptback wing having circular-arc airfoil sections and equipped with drooped-nose and plain flaps
An Investigation of Propeller Vibrations Excited by Wing Wakes
Hydrodynamic Directional Behavior of a Swept Planing-Tail Hull
Damping in Roll of Straight and 45 Degree Swept Wings of Various Taper Ratios Determined at High Subsonic, Transonic, and Supersonic Speeds With Rocket-Powered Models
An Analysis of the Effect of Structural Feedback on the Flutter of a Control Surface Having a Power-Boost System
Effects of spanwise thickness variation on the aerodynamic characteristics of 35 degree and 45 degree sweptback wings of aspect ratio 6: transonic-bump method
The transonic characteristics of 17 rectangular, symmetrical wing models of varying aspect ratio and thickness
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