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National Advisory Committee for Aeronautics Collection
231
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National Advisory Committee for Aeronautics Collection
231
Technical Report Archive and Image Library
231
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NACA Research Memorandums
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NACA Research Memorandums
192
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National Advisory Committee for Aeronautics Collection
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Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel
An experimental study of five annular air inlet configurations at subsonic and transonic speeds
Aerodynamic heating of rocket-powered research vehicles at hypersonic speeds
Some Effects of Fluid in Pylon-Mounted Tanks on Flutter
Rocket-engine throttling
Design procedure for transpiration-cooled strut-supported turbine rotor blades
Preliminary investigation of effect on performance of dividing conical-spike nose inlets into halves at Mach numbers 1.5 to 2.0
Performance and Component Frontal Areas of a Hypothetical Two-Spool Turbojet Engine for Three Modes of Operation
A Study of the Correlation Between Flight and Wind-Tunnel Buffeting Loads
Preliminary investigation at Mach number 1.9 of simulated wing-root inlets
Additional experimental heat-transfer and durability data on several forced-convection, air-cooled, strut-supported turbine blades of improved design
Performance of YJ73-GE-3 turbojet engine in altitude test chamber
Turbojet engine investigation of effect of thermal shock induced by external water-spray cooling on turbine blades of five high-temperature alloys
Performance of several air ejectors with conical mixing sections and small secondary flow rates
Results Obtained During Accelerated Transonic Tests of the Bell XS-1 Airplane in Flights to a Mach Number of 0.92
An Experimental Investigation at Large Scale of Several Configurations of an NACA Submerged Air Intake
Downwash and Dynamic Pressure at the Horizontal Tail of a Six-Engine Pusher-Propelled Airplane
General handling-qualities results obtained during acceptance flight tests of the Bell XS-1 airplane
Use of an Aerodynamically Pulsed All-Movable Horizontal Tail to Obtain Longitudinal Characteristics of Rocket-Powered Models in Free Flight and Some Initial Results From an Arrow-Wing-Body-Tail Configuration
Radiant Heat Transfer From Flames in a Single Tubular Turbojet Combustor
Design and Test of Mixed-Flow Impellers 2: Experimental Results, Impeller Model MFI-1A
Effects on the weight-flow range and efficiency of a typical axial-flow compressor inlet stage that result from the use of a decreased blade camber or decreased guide-vane turning
An analysis of axial- and centrifugal-flow turbojet-engine performance with variable-area exhaust nozzle
Effect of the Proximity of the Ground on the Stability and Control Characteristics of a Vertically Rising Airplane Model in the Hovering Condition
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