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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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Technical Report Archive and Image Library
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NACA Research Memorandums
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National Advisory Committee for Aeronautics Collection
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Stability Results Obtained With Douglas D-558-1 Airplane (BuAero No. 37971) in Flight Up to a Mach Number of 0.89
Test of single-stage axial-flow fan
Photographic investigation of combustion in a two-dimensional transparent rocket engine
Some theoretical low-speed span loading characteristics of swept wings in roll and sideslip
An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds
A Method for Calculating Flow Fields of Cowlings with Known Surface-Pressure Distributions
Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds
Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22 : longitudinal characteristics of a triangular wing and canard
The problem of cooling an air-cooled cylinder on an aircraft engine
Effect of Inlet-Guide-Vane Angle on Blade Vibration and Rotating Stall of 13-Stage Axial-Flow Compressor in Turbojet Engine
Flight investigation of the effect of control centering springs on the apparent spiral stability of a personal-owner airplane
Preliminary investigation of the effects of body contouring as specified by the transonic area rule on the aerodynamic characteristics of a delta wing-body combination at Mach numbers of 1.41 and 2.01
Free-flight performance of 16-inch-diameter supersonic ram-jet units 1: four units designed for combustion-chamber-inlet Mach number of 0.12 at free-stream Mach number of 1.6 (units A-2, A-3, A-4, and A-5)
Investigation of Drag and Static Longitudinal and Lateral Stability and Control Characteristics of 1/20-Scale Model of McDonnell F4H-1 Airplane at Mach Numbers of 1.57, 1.87, 2.16, and 2.53: Phase II Model
Effect of Inlet-Air Parameters on Combustion Limit and Flame Length in 8-Inch-Diameter Ram-Jet Combustion Chamber
Wind-Tunnel Tests of a 0.16-Scale Model of the Douglas MX-656 Airplane at High Subsonic Speeds. 2 - Wing and Fuselage Pressure Distribution
Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: wing and fuselage pressure distribution
Aerodynamic Characteristics of Four Bodies of Revolution Showing Some Effects of Afterbody Shape and Fineness Ratio at Free-Stream Mach Numbers From 1.50 to 1.99
Full-Scale Investigation of Several Jet-Engine Noise-Reduction Nozzles
Aircraft Accidents: Methods of Analysis
Investigation of altitude ignition, acceleration, and steady-state operation with a single combustor of a J47 turbojet engine
The Use of Area Suction for the Purpose of Delaying Separation of Air Flow at the Leading Edge of a 63 Degree Swept-Back Wing
Performance of Compressor of XJ-41-V Turbojet Engine, 4, Performance Analysis Over Range of Compressor Speeds from 5000 to 10,000 RPM
Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine 1 - Preliminary Investigation at 50-,70-, and 100-Percent Design Equivalent Speed
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