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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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1950-1959
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National Advisory Committee for Aeronautics Collection
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Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines
Observations on an aileron-flutter instability encountered on a 45 degree swept-back wing in transonic and supersonic flight
Longitudinal Stability and Drag Characteristics at Mach Numbers From 0.75 to 1.5 of an Airplane Configuration Having a 60 Degree Swept Wing of Aspect Ratio 2.24 as Obtained From Rocket-Propelled Models
Flight Investigation of the Effect of Sideslip on the Pressure at the Static Orifices of the Boeing B-29 Airplane
The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources
An Investigation at Mach Numbers of 1.62 and 1.93 of the Lift Effectiveness and Integrated Downwash Characteristics of Several In-Line Missile Configurations Having Equal-Span Wings and Tails
Effect of inlet-duct length in uniform-flow field on turbojet-engine operation
Design and performance of a 1400-foot-per-second-tip-speed supersonic compressor rotor
Performance of Pure Fuels in Single J33 Combustors 2: Hydrocarbon and Nonhydrocarbon Fuels
Effect of flight speed on dynamics of a turboprop engine
Stabilization Techniques for Ramp-Type Side Inlets at Supersonic Speeds
High-Altitude Performance of an Experimental Turbojet Combustor Having Variable Primary-Air Admission
An analysis of available data on effects of wing-fuselage-tail and wing-nacelle interference on the distribution of the air load among components of airplanes
Preliminary Analysis of a Nuclear-Powered Supersonic Airplane Using Ramjet Engines
Tests of a Horizontal-Tail Model through the Transonic Speed Range by the NACA Wing-Flow Method
The Design of Variable Mach Number Asymmetric Super-Sonic Nozzles by Two Procedures Employing Inclined and Curved Sonic Lines
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds
Component Performance Investigation of J71 Experimental Turbine 2 - Internal-Flow Conditions with 97-Percent-Design Stator Areas
Component performance investigation of J71 experimental turbine 1: Over-all performance with 97-percent-design stator areas
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