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NACA Research Memorandums
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Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26
A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees
Wing-load measurements at supersonic speeds of the Douglas D-558-II research airplane
Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds
Removal of secondary-flow accumulations in a two-dimensional turbine nozzle passage by boundary-layer bleed
Design considerations of a condensing system for vaporized magnesium
Effects of Canopy, Revised Vertical Tail, and a Yaw-Damper Vane on the Aerodynamic Characteristics of a 1/16-Scale Model of the Douglas D-558-II Research Airplane at a Mach Number of 2.01
Wing Pressure Distributions Over the Lift Range of the Convair XF-92A Delta-Wing Airplane at Subsonic and Transonic Speeds
Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a 1/15-Scale Model of the Grumman F11F-1F Airplane at Mach Numbers of 1.56, 1.76, 2.06, and 2.53
A Wind-Tunnel Investigation of the Effects of Conical Camber for an Airplane Configuration Having a Triangular Wing of Aspect Ratio 2.2
Wind-Tunnel Investigation at High Subsonic Speeds of the Effects on Static Stability Characteristics of Various Modifications to a Swept-Wing Fighter-Type Airplane Model
Experimental and theoretical investigation of rotating-stall characteristics of single-stage axial-flow compressor with hub-tip ratio of 0.76
Tabulated pressure data for a series of controls on a 60 degree delta wing at Mach numbers of 1.61 and 2.01
Experimental Investigation of a 0.4 Hub-Tip Diameter Ratio Axial-Flow Compressor Inlet Stage at Transonic Inlet Relative Mach Numbers 3: Effect of Tip Taper on Over-All and Blade-Element Performances
Altitude performance evaluation of J71-A-11 turbojet engine
Preliminary investigation of the effects of several seeker-nose configurations on the longitudinal characteristics of a canard-type missile at a Mach number of 1.60
Experimental Investigation at High Subsonic Speeds of the Rolling-Stability Derivatives of a 1/22 Scale Model of the Republic F-105 Airplane
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Mach Numbers of 1.41, 1.61, and 2.01
Investigation of the Static Stability Characteristics of Five Hypersonic Missile Configurations at Mach Numbers From 2.29 to 4.65
Flight Investigation at Low Angles of Attack to Determine the Longitudinal Stability and Control Characteristics of a Cruciform Canard Missile Configuration With a Low-Aspect-Ratio Wing and Blunt Nose at Mach Numbers From 1.2 to 2.1
Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine: 1: Rotor Blades With 10 Tubes in Cooling-Air Passages
Preliminary Performance Data Obtained in a Full-Scale Free-Jet Investigation of a Side-Inlet Supersonic Diffuser
Analysis of Heat Transfer and Fluid Friction for Fully Developed Turbulent Flow of Supercritical Water With Variable Fluid Properties in a Smooth Tube
Experimental and Theoretical Determination of Forces and Moments on a Store and on a Store- Pylon Combination Mounted on a 45 Degree Swept- Wing-Fuselage Configuration at a Mach Number of 1.61
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