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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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1955
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1955
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National Advisory Committee for Aeronautics Collection
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1955
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The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselagestore Configurations 1. - Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Lift and Drag; Mach Number, 1.61
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder
Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing Model of the Northrop MX-775A Missile with Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail
Preliminary Results From Free Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder
Comparison of two methods of modulating the throat area of convergent plug nozzles
Design and performance of a 1400-foot-per-second-tip-speed supersonic compressor rotor
Analysis of factors affecting selection and design of air-cooled single-stage turbines for turbojet engines 4: coolant-flow requirements and performance of engines using air-cooled corrugated-insert blades
Turbulent Convective Heat-Transfer Coefficients Measured From Flight Tests of Four Research Models (NACA RM-10) at Mach Numbers From 1.0 to 3.6
Performance of Pure Fuels in Single J33 Combustors 2: Hydrocarbon and Nonhydrocarbon Fuels
Flight Measurements of the Transonic Drag of Models of Several Isolated External Stores and Nacelles
Effect of flight speed on dynamics of a turboprop engine
Stabilization Techniques for Ramp-Type Side Inlets at Supersonic Speeds
Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing of the Northrop MX-775A Missile With Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail
High-Altitude Performance of an Experimental Turbojet Combustor Having Variable Primary-Air Admission
Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder
Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102A Airplane at Transonic Speeds
Aerodynamic Design of Axial-flow Compressors 6 - Experimental Flow in Two-Dimensional Cascades
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