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- Aerodynamic Characteristics of a 0.5-Scale Model of the Fairchild XSAM-N-2 Lark Missile at High Subsonic Speeds
- Response of a Rotating Propeller to Aerodynamic Excitation
- Experimental study of flow past turbine blades
- Critical Stress of Ring-Stiffened Cylinders in Torsion
- Vibration Survey of Blades in 10-Stage Axial-Flow Compressor 1: Static Investigation
- Investigations on the Stability, Oscillation, and Stress Conditions of Airplanes With Tab Control: Second Partial Report: Application of the Solutions Obtained in the First Partial Report to Tab-Controlled Airplanes
- Initial Experiments on Flutter of Unswept Cantilever Wings at Mach Number 1.3
- High-Speed Wind-Tunnel Investigation of a Sweptback Wing With an Added Triangular Area at the Center
- General Theory of Aerodynamic Instability and the Mechanism of Flutter
- Aerodynamic characteristics of 15 NACA airfoil sections at seven Reynolds numbers from 0.7 x 10(exp 6) to 9.0 x 10(exp 6)
- Aerodynamic characteristics of the NACA 8-H-12 airfoil section at six Reynolds numbers from 1.8 x 10(exp 6) to 11.0 x 10(exp 6)
- Aerodynamic Properties of Cruciform-Wing and Body Combinations at Subsonic, Transonic, and Supersonic Speeds
- A Statistical Study of Wave Conditions at Four Open-Sea Localities in the North Pacific Ocean
- Ambient Pressure Determination at High Altitudes by Use of Free-Molecule Theory
- Wind-tunnel investigation of the spinning characteristics of a model of a twin-tail low-wing personal-owner-type airplane with linked and unlinked rudder and aileron controls
- The NACA oil-damped V-G recorder
- A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel
- 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 the NACA 4-(0)(03)-45 two-blade propeller at forward Mach numbers to 0.925
- 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
- Investigation of an impulse axial-flow compressor rotor over a range of blade angles
- Low-speed wind-tunnel investigation of a triangular sweptback air inlet in the root of a 45 degree sweptback wing
- Flight calibration of four airspeed systems on a swept-wing airplane at Mach numbers up to 1.04 by the NACA radar-phototheodolite method
- 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
- Effects of Mach number up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of a wing of NACA 66-series airfoil sections
- Preliminary Performance Data on Westinghouse Electronic Power Regulator Operating on J34-WE-32 Turbojet Engine in Altitude Wind Tunnel
- Investigation of High-Subsonic Performance Characteristics of a 12 Degree 21-Inch Conical Diffuser, Including the Effects of Change in Inlet-Boundary-Layer Thickness
- Tests of a Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Stability and Control
- Calibration of Instruments for Measuring Wind Velocity and Direction
- Investigation of Altitude Ignition, Acceleration, and Steady-State Operation with a Single Combustor of a J47 Turbojet Engine
- Gust-Tunnel Investigation to Determine the Load at the Joint of a Coupled Airplane Configuration Encountering a Gust
- Performance of J33-A-27 Turbojet-Engine Compressor, II, Over - All Performance Characteristics of Modified Compressor at Equivalent Impeller Speeds from 6100 to 13,250 RPM
- Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Similar to One Proposed by Douglas Aircraft Company, Inc.
- Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Proposed by All American Airways, Inc.
- Transonic Stability and Control Investigation of a 1/80-Scale Model of the Consolidated Vultee Skate 9 Seaplane, TED No. NACA DE 345: Transonic-Bump Method
- Ditching Investigation of a 1/24-Scale Model of the Boeing B-47 Airplane
- Flight experiences and tests on two airplanes with suction slots
- Icing Characteristics and Anti-Icing Heat Requirements for Hollow and Ternally Modified Gas-Heated Inlet Guide Vanes
- Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures
- Experimental and Analytical Study of Balanced-Diaphragm Fuel Distributors for Gas-Turbine Engines
- Penetration of Air Jets Issuing from Circular, Square, and Elliptical Orifices Directed Perpendicularly to an Air Stream
- Interpretation of boundary-layer pressure-rake data in flow with a detached shock
- Fabrication and Properties of Hot-Pressed Molybdenum Disilicide
- Investigation of frequency-response characteristics of engine speed for a typical turbine-propeller engine
- Investigation of first stage of two-stage turbine designed for free-vortex flow
- Investigation of fretting corrosion by microscopic observation
- First-order theory for unsteady motion of thin wings at supersonic speeds