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NACA Research Memorandums
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Experimental investigation of deposition by boron-containing fuels in turbojet combustor
Free-flight investigation to determine some effects of tail damping and wing-tail interference on the rolling effectiveness of ailerons and a spoiler on a modified-delta wing at Mach numbers from 0.6 to 1.5
Free-flight performance of a rotating-vane-spoiler roll control system with low actuating forces
Investigation of Static Stability and Drag Characteristics of a 1/10-Scale Model of the Avco Booster Vehicle at Mach Numbers of 1.60 and 2.00, Coord. No. AF-AM-58
Performance at High Temperatures and Pressures of an Annular Turbojet Combustor Having Articulated Liner Walls
Free-Flight Skin Temperature and Pressure Measurements on a Slightly Blunted 25 Deg Cone-Cylinder-Flare Configuration to a Mach Number of 9.89
Investigation of an Air-Cooled, Plug-Type, Variable-Area Exhaust Nozzle
Investigation of an Air-Cooled, Plug-Type, Variable-Area Exhaust Nozzle
Lateral-directional aerodynamic characteristics of several coplanar triple-body missile configurations at Mach numbers from 0.6 to 1.4
Longitudinal and Lateral Stability and Control Characteristics of Two Canard Airplane Configurations at Mach Numbers of 1.41 and 2.01
Measurement of Aerodynamic Heat Transfer to a Deflected Trailing-Edge Flap on a Delta Fin in Free Flight at Mach Numbers From 1.5 to 2.6
A Transonic Investigation of the Mass-Flow and Pressure Recovery Characteristics of Several Types of Auxiliary Air Inlets
Experimental Static Aerodynamic Forces and Moments at High Subsonic Speeds on a Missile Model During Simulated Launching From the Midsemispan Location of a 45 Degree Sweptback Wing-Fuselage-Pylon Combination
Measurement of Static Forces on Internally Carried Bombs of Three Fineness Ratios in Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.61 With Illustrative Drop Path Calculations
Measurement of Static Forces on Internally Carried Bombs of Three Fineness Ratios in Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.61 With Illustrative Drop-Path Calculations
Pressure distribution induced on a flat plate by a supersonic and sonic jet exhaust at a free-stream Mach number of 1.80
Static longitudinal characteristics at high subsonic speeds of a complete airplane model with a highly tapered wing having the 0.80 chord line unswept and with several tail configurations
Experimental Investigation of a Five-Stage Axial-Flow Research Compressor With Transonic Rotors in All Stages 3: Interstage Data and Individual Stage Performance Characteristics
Experimental investigation of a high subsonic Mach number turbine having low rotor suction-surface diffusion
Methods for calculating thrust augmentation and liquid consumption for various turbojet-afterburner fuels
Thermodynamic study of air-cycle and mercury-vapor-cycle systems for refrigerating cooling air for turbines or other components
The Appearance of a Boric Oxide Exhaust Cloud From a Turbojet Engine Operating on Trimethylborate Fuel
The appearance of a boric oxide exhaust cloud from a turbojet engine operating on trimethylborate fuel
Force and Pressure-Distribution Investigation to High Angles of Attack on All-Movable Triangular and Rectangular Wings in Combination With a Body at Supersonic Speeds
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