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NACA Research Memorandums
47
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NACA Research Memorandums
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1952
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1952
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An Investigation of the Effect of the WADC 30,000-Horsepower Whirl Rig Upon the Static Characteristics of a Propeller
Summary of Low-Lift Drag and Directional Stability Data from Rocket Models of the Douglas XF4D-1 Airplane with and without External Stores and Rocket Packets at Mach Numbers from 0.8 to 1.38: TED No. NACA DE-349
Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers
A Transonic Wind-Tunnel Investigation of the Aerodynamic Characteristics of Three 4-Percent-Thick Wings of Sweepback Angles 10.8 Degrees, 35 Degrees, and 47 Degrees, Aspect Ratio 3.5, and Taper Ratio 0.2 in Combination With a Body
Preliminary Experiments on the Elastic Compressive Buckling of Plates With Integral Waffle-Like Stiffening
Flow Separation From Rods Ahead of Blunt Noses at Mach Number 2.72
Preliminary air-flow and thrust calibrations of several conical Cooling-air ejectors with a primary to secondary temperature ratio of 1.0 I :diameter ratios of 1.21 and 1.10
Comparison of calculated and experimental temperatures of water-cooled turbine blades
Development of Metal-Bonding Adhesive FPL-710 With Improved Heat-Resistant Properties
Calibration of the Slotted Test Section of the Langley 8-Foot Transonic Tunnel and Preliminary Experimental Investigation of Boundary-Reflected Disturbances
Dynamic corrosion of a stainless-steel specimen by water at 500 degrees F using a toroid circulating apparatus
Effect of trailing edge thickness on lift at supersonic velocities
Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combination at high subsonic speeds: Sweep series
Survey of some preliminary investigations of supersonic diffusers at high Mach numbers
Transonic aerodynamic characteristics of three thin triangular wings and a trapezoidal wing, all of low aspect ratio
An Investigation of the Stream-Tube Power Losses and an Improvement of the Diffuser-Entrance Nose in the Langley 8-Foot Transonic Tunnel
Analysis of V-g records from the Grumman F8F-2 airplane
The Forces and Pressure Distribution at Subsonic Speeds on a Cambered and Twisted Wing Having 45 Degrees of Sweepback and Aspect Ratio of 3 and a Taper Ratio of 0.5
Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane tapered wing of aspect ratio 3.1 with 3-percent-thick rounded-nose section
Solubility of water in hydrocarbons
Reflection of shock waves from slotted walls at Mach number 1.62
Investigation of Turbines for Driving Supersonic Compressors 2: Performance of First Configuration With 2.2 Percent Reduction in Nozzle Flow Area
Low-Speed Wind-Tunnel Investigation of the Effects of Propeller Operation at High Thrust on the Longitudinal Stability and Trim of a Twin-Engine Airplane Configuration
Some effects of body cross-sectional shape, including sunken-canopy design, on drag as shown by rocket-powered-model tests at Mach numbers from 0.8 to 1.5
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