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NACA Research Memorandums
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Numerical solution of equations for one-dimensional gas flow in rotating coolant passages
Supplementary analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass and aerodynamic parameters
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback: Static longitudinal stability and control characteristics at a Mach number of 1.59
Heat-transfer and operating characteristics of aluminum forced-convection and stainless-steel natural-convection water-cooled single-stage turbines
Effect of Compressibility and Camber as Determined From an Investigation of the NACA 4-(3)(08)-03 and 4-(5)(08)-03 Two-Blade Propellers Up to Forward Mach Numbers of 0.925
Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet
Low-speed investigation of leading-edge and trailing-edge flaps on a 47.5 degree sweptback wing of aspect ratio 3.4 at a Reynolds number of 4.4 x 10(exp 6)
A Design Study of Leading-Edge Inlets for Unswept Wings
Tank investigation of the Grumman JRF-5 airplane fitted with hydro-skis suitable for operation on water, snow, and ice
Preliminary Analysis of Problem of Determining Experimental Performance of Air-Cooled Turbine 1: Methods for Determining Heat-Transfer Characteristics
Preliminary Analysis of Problem of Determining Experimental Performance of Air-Cooled Turbine 2: Methods for Determining Cooling-Air-Flow Characteristics
Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds: wing and fuselage pressure distribution
Free-Flight Performance of 16-Inch-Diameter Supersonic Ram-Jet Units 3: Four Units Designed for Combustion-Chamber-Inlet Mach Number of 0.245 at Free-Stream Mach Number of 1.8 (Units D-1, D-2, D-3, and D-4)
Effect of blade-root fit and lubrication on vibration characteristics of ball-root-type axial-flow-compressor blades
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Lateral Stability Characteristics at Mach Numbers of 1.40 and 1.59
Large-scale flight measurements of zero-lift drag at Mach numbers form 0.86 to 1.5 of a wing-body combination having a 60 degree triangular wing with NACA 65A003 sections
Longitudinal-stability characteristics of the Northrop X-4 airplane (USAF No. 46-677)
Low-Speed Investigation of Deflectable Wing-Tip Elevators on a Low-Aspect-Ratio Untapered 45 Degree Sweptback Semispan Wing With and Without an End Plate
Range Performance of Bombers Powered by Turbine-Propeller Power Plants
Wind-tunnel tests of a 0.16-scale model of the X-3 airplane at high subsonic speeds : additional stability and control characteristics and the aerodynamic effects of external stores and ram jets
Investigation of the NACA 3-(3)(05)-05 Eight-Blade Dual-Rotating Propeller at Forward Mach Numbers to 0.925
Performance of J33-A-27 Turbojet-Engine Compressor, III, Over-All Performance Characteristics of Modified Compressor with Water Injection at Design Equivalent Speed of 11,800 RPM
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